42nd week of 2017 patent applcation highlights part 31 |
Patent application number | Title | Published |
20170298728 | Chisel Holder - A chisel holder has an outer sleeve, a holding member, multiple positioning members, a resilient member, and a limiting ring. The outer sleeve has an assembling space, a receiving chamber, and an abutting rib. The receiving chamber is defined in the outer sleeve at a position adjacent to the top of the outer sleeve and is conical. The holding member is mounted in the outer sleeve and has a central hole, a limiting rib, and multiple holding holes. The positioning members are mounted respectively in the holding holes in the holding member, selectively extend into the central hole in the holding member, and abut an inner surface of the receiving chamber. The resilient member is mounted in the assembling space in the outer sleeve and abuts the bottom of the holding member. | 2017-10-19 |
20170298729 | INTEGRATED JACKING PIPES - An integrated jacking pipe comprising a concrete jacking envelope integrally-formed with and encircling a metal pipe, wherein said metal pipe comprises a spigot protruding from said concrete jacking envelope and a bell whose diameter is larger than a diameter of said spigot. | 2017-10-19 |
20170298730 | CUTTING APPARATUS - A cutting apparatus suitable for creating tunnels and subterranean roadways includes independently pivoting supports that each carry a respective independently pivoting arm and a rotatable cutting head. Each cutting head, via the supports and arms, is configured to slew laterally outward in a sideways direction and to pivot in a vertical upward and downward direction. The supports and arms are mounted on a linear moving sled carried by a main frame. | 2017-10-19 |
20170298731 | DEVICE FOR THE INSTALLATION OF ROCK BOLTS AND CUTTING APPARATUS - A device for the installation of rock bolts includes a supporting structure and first and second bolting units mounted to the supporting structure. Each bolting unit is configured for drilling an installation hole and/or for installing a rock bolt into a rock face, wherein the supporting structure is configured for rotatably moving the first and second bolting units about a common axis of rotation. At least one actuator is mounted to the supporting structure and configured for additionally moving at least one of the first and second bolting units. | 2017-10-19 |
20170298732 | ROCK BOLT - A rock bolt to be embedded in a borehole and a method of manufacturing a rock bolt, the rock bolt including an extended energy-absorbing part, the first end of the energy-absorbing part including an anchor and the second end of the energy-absorbing part including a screw joint for prestressing the rock bolt. The rock bolt includes an extended tubular part with a jacket and a first end section and a second end section, with an internal dimension that is larger than the external dimension of the energy-absorbing part and arranged in such a manner that it surrounds the energy-absorbing part. | 2017-10-19 |
20170298733 | COMPOSITE MOLDED ROTARY COMPONENT - The present teachings generally include a composite rotor assembly comprising a shaft and a rotor body mounted to the shaft. The rotor body can include a core structure including a cured polymeric material wholly or partly defining plurality of lobes joined by adjacent root portions. The rotor body can also include a support structure continuously extending the length of the core structure to provide additional structural integrity to the rotor body. The support structure can be wholly or partially embedded within the core structure and can also be wrapped around the exterior of the core structure. In one example, the core structure includes an epoxy resin and the support structure includes a carbon fiber material. | 2017-10-19 |
20170298734 | ROTARY ACTUATOR - A cylinder is installed within a case, and an output shaft and an arm that is integrated thereto and extends in a radial direction are installed within the cylinder. A piston extending in an arc slides and is displaced in a circumferential direction of the cylinder within the cylinder. One end portion of the piston is rotatably connected to the arm. The cylinder is internally provided with a first pressure chamber in which the arm is housed and a second pressure chamber in which the other end portion of the arm is slidably installed. A pressure medium is fed into one of the first and second pressure chambers and discharged from the other, and the output shaft pivots in a rotational direction. | 2017-10-19 |
20170298735 | AIRCRAFT ENGINE ROTOR REPAIRED WITH MICROSTRUCTURAL ENHANCEMENT - A rotor for use in an aircraft engine, that has been repaired by (a) welding together a first portion of a damaged blade of the rotor and a second portion of metal to form a weld nugget, (b) compressively stressing the weld nugget throughout its volume, and (c) heat treating the compressively stressed weld nugget to recrystallize metal therein. | 2017-10-19 |
20170298736 | RADIAL TURBOMACHINE - A radial turbomachine has: a fixed casing; at least one rotor disc installed in the casing and rotatable in the casing around a respective rotation axis; a plurality of annular rotor elements coaxial with the rotation axis, axially projecting from a front face of the rotor disc and/or from a rear face of the rotor disc; a plurality of annular fixed elements coaxial with the rotation axis, axially projecting from the casing and each positioned in a radially external position with respect to a respective annular rotor element; a plurality of sealing devices radially interposed between at least some of said annular rotor elements and the respective annular fixed elements. | 2017-10-19 |
20170298737 | TURBOMACHINE - A turbomachine includes a turbine impeller having a rotational axis, a first end portion, and a second end portion. The turbine impeller includes main blades and splitters. Each of the main blades has a blade first edge provided at the first end portion and a blade second edge provided at the second end portion and extends from the blade first edge to the blade second edge. Each of the splitters has a splitter first edge and a splitter second edge and extends from the splitter first edge to the splitter second edge. The blade first edge and the splitter first edge are arranged on a plane perpendicular to the rotational axis. The splitter second edge is positioned between the splitter first edge and the blade second edge along the rotational axis. The main blades and the splitters are arranged alternately in a circumferential direction around the rotational axis. | 2017-10-19 |
20170298738 | CONTROLLED COOLING OF TURBINE SHAFTS - A turbomachine, in particular a steam turbine, has a shield and a coolant supply which causes cold intermediate superheater steam to flow onto the rotor, wherein additionally supply holes are arranged in the shield, which holes bring part of the hot inflow steam into the cooling region between the shield and the rotor, in order to thus improve mixing so as to raise the temperature of the rotor at this thermally loaded point, such that in the event of a fault (e.g., failure of the coolant line) the resulting change in temperature is moderate. | 2017-10-19 |
20170298739 | Bolt On Seal Ring - A device to route cooling air to a turbine blade is provided. The device includes a seal ring having an L-shaped cross section configured to abut a turbine disc. The seal ring includes a radial portion extending radially with respect to a rotor and an axial portion extending axially with respect to the rotor. The seal ring also includes a plurality of radial cooling holes disposed within the radial portion of the seal ring and arranged circumferentially around the seal ring. The plurality of cooling holes route cooling air from a device configured to impart tangential momentum to the cooling air to a turbine blade in order to cool the turbine blade. A system and a method to improve a flow of rotor cooling air to a turbine blade are also provided. | 2017-10-19 |
20170298740 | Noise Reduction to the Trailing Edge of Fluid Dynamic Bodies - A fluid dynamic body having a trailing edge with a pattern formed thereon, the pattern can include a plurality of smoothly surfaced adjacent members with respective interstices therebetween, wherein at least one of the interstices completely contains a porous barrier. In some embodiments, the porous barrier can obstruct fluid flow through the respective interstice between a first surface of the fluid dynamic body on a first side of the trailing edge and a second surface of the fluid dynamic body on a second side of the trailing edge. This helps to reduce noise produced at the trailing edge. In some embodiments, the fluid dynamic body is a wind turbine blade or an air-engine blade. | 2017-10-19 |
20170298741 | STATOR OF AN AIRCRAFT TURBINE ENGINE - A stator of an aircraft turbine engine, comprising an annular row of fixed vanes and an annular row of arms, wherein the trailing edges of the fixed vanes are positioned substantially in a first transverse plane that is positioned downstream of a second transverse plane that passes substantially through the leading edges of the arms. | 2017-10-19 |
20170298742 | TURBINE ENGINE AIRFOIL BLEED PUMPING - An apparatus and method of minimizing airfoil boundary layer separation utilizing at least one bleed inlet disposed on the outer wall of the airfoil, such as the suction side, having at least one channel disposed within an interior of the airfoil providing fluid communication between the bleed inlet and the tip of the airfoil. Bleed gas drawn through the bleed inlet and provided to the tip can pressurize a seal disposed at the tip. Additionally, a flow control device can be disposed within the channel to control or meter the rate at which gas is bled into the channel. | 2017-10-19 |
20170298743 | COMPONENT FOR A TURBINE ENGINE WITH A FILM-HOLE - An apparatus and method relating to a film-hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film-hole. | 2017-10-19 |
20170298744 | SYSTEM FOR COOLING SEAL RAILS OF TIP SHROUD OF TURBINE BLADE - A turbine blade includes a tip shroud having a seal rail. The seal rail includes a tangential surface extending between tangential ends. The turbine blade includes a root portion configured to couple to a rotor and an airfoil portion extending between the root portion and the tip shroud. The seal rail includes a cooling passage extending along a length of the seal rail. The cooling passage is fluidly coupled to a cooling plenum to receive a cooling fluid via an intermediate cooling passage extending between the cooling passage and a cooling plenum. The seal rail includes cooling outlet passages fluidly coupled to the cooling passage. The cooling outlet passages are disposed within the seal rail and extend between the cooling passage and the tangential surface of the seal rail. The cooling outlet passages are configured to discharge the cooling fluid from the tip shroud via the tangential surface. | 2017-10-19 |
20170298745 | FIBER REINFORCED AIRFOIL - An airfoil and a method of manufacturing an airfoil may be provided, where the airfoil comprises a core and a shell. The core comprises core ceramic fibers extending along a span of the airfoil. The shell surrounds the core and includes shell ceramic fibers. Substantially all of the core ceramic fibers are arranged in a radial direction. The airfoil may also be a ceramic matrix composite formed by infiltrating the core and the shell with a matrix material. | 2017-10-19 |
20170298746 | TURBINE ENGINE GUIDE VANE - The present invention relates to a turbine engine guide ( | 2017-10-19 |
20170298747 | GAS TURBINE ENGINE TRANSITION DUCT AND TURBINE CENTER FRAME - A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 50% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils. | 2017-10-19 |
20170298748 | GAS TURBINE ENGINE WITH COMPLIANT LAYER FOR TURBINE VANE ASSEMBLIES - A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component. | 2017-10-19 |
20170298749 | MACHINING PROCESS FOR MULTI-VANE NOZZLE - The present invention relates to a method for machine finishing the shape of a blank casting for a multi-vane, in particular bi-vane, nozzle of a turbine engine, comprising a first vane and a second vane extending substantially in a radial direction between two walls that are radially inner and radially outer, respectively, the suction face of the first vane defining, together with the pressure face of the trailing edge of the second vane, a cross section of flow (SP), the method comprising measuring, by means of probing, the position of predefined points on said respectively radially inner and radially outer walls on the surface of the vanes and calculating the machining allowances (Δ1 and Δ2 respectively) on the first and second vanes with respect to the theoretical profile at said points, wherein the method comprises calculating said cross section of flow (SP) from the height of the duct between said radially inner and radially outer walls, and values of the machining allowances (Δ1 and Δ2), a correction of the machining allowance (Δ2) on one of the vanes being applied when the calculated value of the cross section of flow (SP) is outside predefined tolerances. | 2017-10-19 |
20170298750 | VANE WITH SPOILER - Relates to a vane for a turbomachine. The vane ( | 2017-10-19 |
20170298751 | MODULAR TURBINE VANE - An airfoil attachment system ( | 2017-10-19 |
20170298752 | GAS BEARING SEAL - A turbomachine includes a compressor section, a turbine section, and a rotary component. The rotary component is attached to and rotatable with a portion of at least one of the compressor section and the turbine section. The turbomachine additionally includes a seal having a gas bearing. The gas bearing defines an inner surface along a radial direction of the turbomachine, a high pressure end, and a low pressure end. The gas bearing supports the rotary component and also prevents an airflow from the high pressure end to the low pressure end between the rotary component and the inner surface of the gas bearing. | 2017-10-19 |
20170298753 | TURBINE SHROUD WITH SEALED BOX SEGMENTS - A turbine shroud adapted to extend around a bladed turbine wheel to block gasses from passing over the bladed turbine wheel is disclosed. In a segmented embodiment, each turbine shroud segment may include a carrier segment and a blade track segment. The carrier segment may comprise metallic materials and may be formed to define an attachment-receiving space. The blade track segment may comprise ceramic matrix composite materials and may be formed to include an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment. | 2017-10-19 |
20170298754 | CONTRA-FLOW STRIPS, CONTRA-FLOW SEAL SEGMENTS, AND METHODS FOR INHIBITING LEAKAGE - A contra-flow strip for inhibiting leakage of a fluid between a rotating member and a stationary member includes, for example, a base supportable by the stationary member coaxially around the rotating member, and means, extending from the base coaxially towards the rotating member between a low pressure region and a high pressure region, for generating a contra flow of a portion of a tangential flow of fluid in the low pressure region to the high pressure region between the stationary member and the rotating member. | 2017-10-19 |
20170298755 | COMPRESSOR SYSTEM - A compressor system ( | 2017-10-19 |
20170298756 | Stand Alone Hydro Electric Power Supply System - A “Hydro Electric Power Supply System” that comprises an upper water tank and a lower water tank. The tanks are positioned where the said upper water tank is placed above the said lower water tank to create a necessary water flow from top to bottom. Also used is a water pump; a first turbine to generate electricity dedicated to power the water pump so as to extract water from said lower water tank back up to said upper water tank. There is also the ability within this device for a second turbine to generate electricity for consumer usage. A plurality of pipes are also incorporated so as to create water passages between said upper water tank, said first and second turbine, and said water pump. | 2017-10-19 |
20170298757 | GEARED ARCHITECTURE FOR HIGH SPEED AND SMALL VOLUME FAN DRIVE TURBINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and a gear system is connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. At least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness. | 2017-10-19 |
20170298758 | AEROFOIL BODY - An aerofoil body for a gas turbine engine is provided. The aerofoil body has leading and trailing edge portions, wherein one of the leading and trailing edge portions is a morphable edge portion having a composite layer structure. The aerofoil body further has a non-morphing central portion which forms pressure and suction surfaces of the aerofoil body between the leading and trailing edge portions. The composite layer structure includes a return spring, one or more shape memory alloy layers, and a flexible cover for the return spring and the one or more shape memory alloy layers. The flexible cover defines pressure and suction surfaces of the aerofoil body at the morphable edge portion. The one or more shape memory alloy layers are electrically heatable to deform the layers against the resistance of the return spring, and thereby alter the pitch of the aerofoil body at the morphable edge portion. | 2017-10-19 |
20170298759 | FAILURE DETECTION DEVICE - The failure detection device includes an accumulated data storage unit | 2017-10-19 |
20170298760 | Axial Turbine Engine Compressor De-Icing Blade - An aeroplane turbojet low-pressure compressor vane includes a leading edge, a trailing edge, a surface, and an extrados surface which extend from the leading edge to the trailing edge. To combat the presence and the formation of ice, the vane is provided with an electric de-icing device with a thermistor. The thermistor forms a heating electrical track suitable for de-icing the vane. The present application also proposes a method for producing a turbine engine vane. | 2017-10-19 |
20170298761 | HEAT SHIELD - A heat shield ( | 2017-10-19 |
20170298762 | GAS TURBINE ENGINE TURBINE VANE BAFFLE AND SERPENTINE COOLING PASSAGE - An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity. | 2017-10-19 |
20170298763 | MOUNTING ARRANGEMENT FOR MOUNTING A FLUID COOLER TO A GAS TURBINE ENGINE CASE - A mounting arrangement for mounting a fluid cooler to an engine case of a gas turbine engine, the mounting arrangement comprises at least one fixture adapted to be mounted to the engine case and defining a circumferentially extending channel for receiving at least one circumferentially extending flange of a cooler body of the fluid cooler. The at least one flange being free to slide in the channel of the at least one fixture in a circumferential direction of the engine case. The fixture may further comprise a clamping arrangement to hold the fluid cooler while allowing the same to thermally grow. | 2017-10-19 |
20170298764 | COMPARTMENTALIZATION OF COOLING AIR FLOW IN A STRUCTURE COMPRISING A CMC COMPONENT - A structure in a gas turbine engine comprises a spar and a CMC component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air. | 2017-10-19 |
20170298765 | FLUID-FILLED DAMPER FOR GAS BEARING ASSEMBLY - The present disclosure is directed to a gas-lubricated bearing assembly for a gas turbine engine and method of damping same. The bearing assembly includes a bearing pad for supporting a rotary component and a bearing housing attached to or formed integrally with the bearing pad. The bearing housing includes a first fluid damper cavity, a second fluid damper cavity in restrictive flow communication with the first fluid damper cavity via a restrictive channel configured as a clearance gap, and a damper fluid configured within the first and second fluid damper cavities. More specifically, the damper fluid of the present disclosure is configured to withstand the high temperature environment of the engine. Thus, the bearing housing is configured to transfer the damper fluid from the first fluid damper cavity to the second fluid damper cavity via the restrictive channel in response to a force acting on the bearing pad. | 2017-10-19 |
20170298766 | THRUST BEARING - A bearing including a bearing pad and a housing is provided. The bearing pad has a thrust face for supporting a vibration along an axial direction of the bearing. Additionally, the housing is formed integrally using an additive manufacturing process and is attached to or formed integrally with the bearing pad. The housing defines a working gas delivery system for providing a flow of pressurized working gas to the thrust face of the bearing pad and a fluid damper cavity. The fluid damper cavity provides a dampening of the axial vibration supported by the thrust face of the bearing pad along the axial direction. | 2017-10-19 |
20170298767 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES - A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area. | 2017-10-19 |
20170298768 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft defining a fan shaft support lateral stiffness and a fan shaft support transverse stiffness and a gear system connected to the fan shaft having a reduction ratio of greater than 2.3. A flexible support supports the gear system and defines a flexible support lateral stiffness and a flexible support transverse stiffness. A low fan pressure ratio of less than 1.45 measured across the fan blades alone. At least one of the flexible support lateral stiffness is less than 11% of the fan shaft support lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness. | 2017-10-19 |
20170298769 | BEARING STRUCTURE OF TURBOCHARGER - An object of the present invention is to provide a bearing structure of a turbocharger that can prevent generation of unusual noise and a decrease in operation efficiency and that can reduce manufacturing costs. The bearing structure of a turbocharger to accomplish such an object, includes a rotor shaft, a ball bearing, a retainer, and a housing. The rotor shaft is provided with a turbine impeller mounted on a first end and a compressor impeller mounted on a second end. | 2017-10-19 |
20170298770 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness, a gear mesh defining a gear mesh lateral stiffness, and a reduction ratio greater than 2.3. A bypass ratio is greater than 10 (10). The ring gear lateral stiffness is less than 12% of the gear mesh lateral stiffness. | 2017-10-19 |
20170298771 | Flow Strakes for Turbocharger Bearing Housing Oil Core - A bearing housing for a turbocharger is disclosed. The bearing housing includes a first end proximate to a turbine wheel of the turbocharger and a second end proximate to a compressor wheel of the turbocharger. The bearing housing further includes a central chamber disposed between the first end and the second end and configured to house, at least, the shaft. The bearing housing further includes an oil drain disposed radially outward of the shaft and configured for directing oil out of the bearing housing and an oil core disposed radially outward of the shaft and radially inward of the oil drain, the oil core configured for communicating oil towards the oil drain and having an inner wall. The bearing housing includes one or more strakes protruding radially inward from the inner wall, the one or more strakes configured to direct oil within the oil core towards the oil drain. | 2017-10-19 |
20170298772 | ROTARY MACHINE WITH GAS BEARINGS - A rotary machine for an aeronautical device includes a thrust generator. The rotary machine additionally includes a rotary component rotatable with the thrust generator. Moreover, the rotary machine of the present disclosure includes a plurality of gas bearings, with the plurality of gas bearings substantially completely supporting the rotary component of the rotary machine. | 2017-10-19 |
20170298773 | BEARING HAVING INTEGRALLY FORMED COMPONENTS - Embodiments of a stage for a turbomachine have been provided herein. In some embodiments, a stage for a turbomachine may include a bearing having a housing, the bearing defining an interior cavity; an outer ring disposed radially outward from the housing; and a plurality of airfoils disposed between the housing of the bearing and the outer ring. | 2017-10-19 |
20170298774 | COUPLING ASSEMBLY FOR COMPONENTS OF CERAMIC MATRIX COMPOSITES FOR A TURBINE CENTER FRAME - A coupling assembly, including a first component and a second component overlapping one another in a join region; a joining device allowing the first component and the second component to rest against each other clampingly in the join region; the joining device including a clamp resting on the first component and the second component and having a bolt connection adapted for securing the clamp to the first and second component. The first component and the second component are manufactured from a ceramic matrix composite; the first component having a holding portion including a front side facing the clamp, a rear side facing away from the clamp, and a receiving opening; and the bolt connection having a bolt portion that extends through the receiving opening and, at the end thereof facing away from the clamp, having a bracing portion that is angled relative to the longitudinal axis of the bolt portion and that rests against the rear side of the holding portion. | 2017-10-19 |
20170298775 | ASSEMBLY OF TWO PARTS COMPRISING A REMOVABLE CENTRING SEAT FOR AN AIRCRAFT TURBINE ENGINE - A turbine engine for an aircraft which includes, in general, at least one assembly made up of a first part wherein a second part is attached with an attachment device including a milled head applied to the first part and a body engaging with the second part in order to clamp the parts. The recess of the head of such an attachment device requires a boss on the first part, which is complex and expensive to produce using conventional techniques. Such a boss can be replaced with a removable seat having an opening through which the body passes and forming a recess for the head, a bearing surface for the head, and abutment device applied to the first part in order to prevent a movement of the seat towards the second part. | 2017-10-19 |
20170298776 | BLADE OUTER AIR SEAL HAVING RETENTION SNAP RING - A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support. | 2017-10-19 |
20170298777 | GAS TURBINE ENGINE ASSEMBLIES WITH CERAMIC MATRIX COMPOSITE COMPONENTS HAVING UNDULATED FEATURES - An assembly adapted for use in a gas turbine engine is disclosed herein. The assembly includes a first component including metallic materials and a second component including ceramic matrix composite materials. A portion of the second component is configured to engage a portion of the first component directly so that the second component is supported in a predetermined position. | 2017-10-19 |
20170298778 | ASSEMBLING AID FOR ASSEMBLING/DE-ASSEMBLING A TURBINE ASSEMBLY - An assembling aid for assembling or de-assembling a turbine assembly having at least two aerofoil assemblies connected to each other by at least two interlocking platforms, wherein the at least two aerofoil assemblies are brought from a free-state untwisted position to an assembled twisted position during assembling, including at least one slot embodied to receive at least one part of an aerofoil assembly, wherein the at least one slot has an entry aperture and an exit aperture. A width of the entry aperture of the at least one slot is wider than a width of the exit aperture of the at least one slot. | 2017-10-19 |
20170298779 | Tooling For Partial Disassembly Of A Bypass Turbofan Engine - Tooling for partial disassembly of a bypass turbofan engine wherein the longitudinal axis of the bypass turbofan engine remains generally horizontal during disassembly. The low pressure turbine module is removed with a low pressure turbine module horizontal removal tool. An extended bearing nut tool may be supported by a stabilization member and may remove a bearing nut. An extended high pressure turbine shaft stretching tool may stretch a high pressure turbine shaft to release a high pressure turbine shaft nut. An extended bearing pulling tool may be used to pull a bearing while the low pressure turbine shaft remains in place. A modified measurement bridge may be used to measure the position of certain components while the low pressure turbine shaft remains in place. A nozzle jig may be used to assemble nozzles and feather seals to create a nozzle module. And an arcuate datum may be used to make certain measurements from the aft end of the high pressure turbine shaft while the low pressure turbine shaft remains in place. | 2017-10-19 |
20170298780 | THERMAL ENERGY RECOVERY DEVICE AND OPERATING METHOD OF THE SAME - A thermal energy recovery device includes: a circulation line having an evaporator, an expander, a condenser, and a pump; a power recovery machine; a first on-off valve; a thermal energy introduction line configured to introduce a gas phase working medium into a post-expansion space; a second on-off valve; and a control unit. Until an evaporation condition that a liquid phase working medium accumulated in the post-expansion space has reached an amount equal to or smaller than a reference amount is met, the control unit closes the first on-off valve and opens the second on-off valve, and drives the pump in a state where the expander is stopped, and when the evaporation condition is met, the control unit opens the first on-off valve and closes the second on-off valve, and drives the expander. | 2017-10-19 |
20170298781 | Strain Augmented Thermodynamic Power Cycle - Strain augmented power cycle is disclosed. This power cycle is a thermodynamic power cycle that contains a strain energy device to increase the thermodynamic efficiency above what is possible from a conventional Rankine power cycle. Strain augmented power cycle comprises an assembly of components including a working fluid, a pump, an evaporator, a strain energy device, an expander and a condenser. | 2017-10-19 |
20170298782 | SYSTEM AND METHOD FOR INCREASING THE RESPONSIVENESS OF A DUCT FIRED, COMBINED CYCLE, POWER GENERATION PLANT - A system and method for increasing the responsiveness of a duct fired, combined cycle power generation plant ( | 2017-10-19 |
20170298783 | METHOD FOR COATING THE NOSE OF THE CAMS OF A CAMSHAFT WITH DLC, CAMSHAFT OBTAINED IN THIS WAY AND FACILITY FOR IMPLEMENTING SAID METHOD - A cam treatment to reduce the friction coefficient thereof relative to a counterpart in an area provided with a hard coating made from amorphous Diamond-Like Carbon or DLC, involves disposing the cams on a support, bringing the support and the cams into a chamber placed under vacuum so as to clean the cams, bringing the support into relative movement along a trajectory of travel relative to a coating source, and taking the cams off the support before assembling them on a camshaft; the method involves disposing the cams on the support in a fixed configuration which is defined in such a way that the cams are brought successively opposite the source with orientations and at distances substantially identical relative to the source, to deposit a hard coating made from amorphous Diamond-Like Carbon or DLC, selectively on the fraction of the section of the cams that is oriented towards the source. | 2017-10-19 |
20170298784 | VALVE GEAR FOR ENGINE - A valve gear for an engine includes camshaft supports, a camshaft, a rocker housing separate from the cam shaft supports, a rocker shaft, a first rocker arm, and a second rocker arm selectively connected to the first rocker arm by switch pins. The valve gear includes a second switch pin and a hydraulic piston that presses the switch pins, and first and second hydraulic supplies that apply an oil pressure to the pistons. The second switch pin is provided in a second rocker arm, and the hydraulic piston is provided in the rocker housing. The first hydraulic supply includes a first oil passage in the second rocker arm, the rocker shaft, and the rocker housing. The second hydraulic supply includes a second oil hole in the rocker housing. | 2017-10-19 |
20170298785 | ROCKER ARM ASSEMBLY AND COMPONENTS THEREFOR - A switching rocker arm system includes a rocker assembly having a first end and a second end, and engaging a lash adjuster an and engine valve. The system further includes a first arm rotationally coupled to a second arm at the first or second end, and selectively rotationally coupled to the second arm at the other of the first end and the second end by a latch. In the latched position, a second cam engagement surface of the second arm engages the second cam to operate the engine valve in a high-lift mode, a biasing spring urges the second cam engagement surface into contact with the second cam, and a rotational stop prevents contact of the second cam engagement surface with a base circle portion of the second cam in the low-lift mode. | 2017-10-19 |
20170298786 | VARIABLE VALVE DRIVE HAVING A ROCKER LEVER - The present disclosure relates to a variable valve drive for a lifting valve, in particular for a charge-exchange valve of an internal combustion engine, which is periodically movable between a closed position and an open position indirectly by way of a cam via a rocker lever. The variable valve drive includes a switchable rocker lever arrangement for the actuation of the lifting valve, having a transmission rocker lever and a valve rocker lever which are mounted pivotably on different rocker lever axles which are each parallel to the camshaft axis. | 2017-10-19 |
20170298787 | VALVE GEAR FOR ENGINE AND METHOD OF MANUFACTURING ROCKER ARMS - A valve gear for an engine includes a camshaft including a cam, a rocker shaft, and a first rocker arm which swings when pressed by the cam. The valve gear includes a spring, which biases the first rocker arm and a second rocker arm which presses an intake valve or an exhaust valve, in a return direction. The valve gear includes a first pin hole of the first rocker arm, a second pin hole and a third pin hole of the second rocker arm, a first switch pin, a second switch pin, a third switch pin, and a switch which switches between a connected state and a non-connected state of the switch pins. The second rocker arm includes a stopper against which the first rocker arm abuts. When the first rocker arm abuts against the stopper, all of the pin holes are located on the same axis. | 2017-10-19 |
20170298788 | VALVE OPENING/CLOSING TIMING CONTROL APPARATUS - A valve opening/closing timing control apparatus includes: a driving side rotating body rotating synchronously with a crankshaft of an internal combustion engine; a driven side rotating body included in the driving side rotating body and rotating integrally with a camshaft on a same axis as a rotation axis of the driving side rotating body; a hydraulic fluid control mechanism displacing a relative rotation phase between the driving side rotating body and the driven side rotating body by supplying a hydraulic fluid to one of an advance angle chamber and a retardation angle chamber; a lock mechanism; and first and second unlocking flow paths configured to communicate with the first pressure receiving surface. The lock mechanism includes a lock member including an engaging portion, a main body portion, and a first pressure receiving surface a biasing member, and a lock recess. | 2017-10-19 |
20170298789 | GASKET FOR A VALVE OF AN INTERNAL COMBUSTION ENGINE - A gasket for a valve of an internal combustion engine is described. The valve has a guide element defining a through seat, and a stem movable in a sliding manner in said seat. The gasket has a central axis and comprises: an elastically deformable sealing element, having an annular configuration with respect to the axis and suitable to be arranged externally on the valve to cooperate both with the guide element and with the stem; a supporting member having an annular configuration, arranged coaxially on at least part of the sealing element so that the latter is pressed radially between the supporting member and the valve; an end flange projecting radially outwards from the supporting member and configured to receive the elastic load of a coil spring of the valve; and protruding means distinct from the flange, projecting outwards from the supporting member and suitable to cooperate with the spring of the valve to maintain it coaxial with the axis. | 2017-10-19 |
20170298790 | HIGHLY THERMALLY CONDUCTIVE VALVE SEAT RING - The invention relates to a powdermetallurgically produced valve seat ring having a carrier layer and a function layer. It is the objective of the invention to provide a valve seat ring of the kind mentioned above that offers significantly higher thermal conductivity properties. To achieve this objective and based on a valve seat ring of the kind first mentioned above the invention proposes that the carrier material of the carrier layer has a thermal conductivity higher than 55 W/m*K at a total copper content ranging between >25 and 40% w/w. | 2017-10-19 |
20170298791 | VALVE LIFT ASSEMBLY FOR A CAM-IN-BLOCK ENGINE - An engine includes a block containing multiple valves, and a camshaft defining multiple cams for rotation about a camshaft axis. A valve lift assembly is operatively associated with a respective one of the cams and a respective one of the valves to transfer motion from the cam to the valve by reciprocal motion of the valve lift assembly along a lift axis. The assembly includes a follower and a follower control mechanism. The follower is disposed in contact with the cam at a contact point that defines a contact path extending along a surface of the cam as the cam rotates about the camshaft axis. The follower is moveable through an adjustment range to change the position of the contact point along the contact path at a given angular position of the cam. The follower control mechanism is operable to control the movement of the follower within the adjustment range. | 2017-10-19 |
20170298792 | OIL LEAKAGE RECOVERY SYSTEM FOR GAS TURBINE ENGINE - An oil leakage recovery system for recovering leaked oil in an oil system of a gas turbine engine The oil leakage recovery system includes a collecting reservoir having an inlet opening and an outlet opening each communicating with the oil system, a piston operatively mounted with the collecting reservoir and movable between a first position in which the piston is disposed away from the outlet opening to allow oil to leak from the collecting reservoir to the oil system and a second position in which the piston blocks the outlet opening to impede oil leaking from the collecting reservoir from the collecting reservoir to the oil system, and a pressure-controlled actuator system configured to move the piston to the first position when a pressure of the oil system is below a threshold pressure value and to the second position when the pressure of the oil system is above the threshold pressure value. | 2017-10-19 |
20170298793 | SELECTIVELY TUNABLE EXHAUST NOISE ATTENUATION DEVICE - A selectively tunable exhaust noise attenuation device includes a body having an outer surface and an inner surface that defines an exhaust volume. An inlet is coupled to the body and fluidically connected to the exhaust volume. A first outlet is coupled to the body and fluidically connected to the inlet and selectively fluidically connected to the exhaust volume and a second outlet coupled to the body and fluidically connected to the exhaust volume. A first conduit including a primary exhaust gas flow path directly fluidically connects the inlet and the first outlet. A second conduit includes a first end and a second. The second conduit defines a secondary exhaust gas flow path. A valve is fluidically connected to one of the first and second conduits. The valve is arranged laterally off-set of the primary exhaust gas flow path. | 2017-10-19 |
20170298794 | CERAMIC HONEYCOMB STRUCTURE AND ITS PRODUCTION METHOD - A ceramic honeycomb structure having pluralities of flow paths partitioned by porous cell walls; (a) the cell walls having porosity of 50-60%; and (b) in a pore diameter distribution in the cell walls measured by mercury porosimetry, (i) pore diameters at cumulative pore volumes corresponding to particular percentages of the total pore volume being within specific ranges and having specific relationships; and (ii) the difference between a logarithm of the pore diameter at a cumulative pore volume corresponding to 20% of the total pore volume and a logarithm of the pore diameter at 80% being 0.39 or less, and its production method. | 2017-10-19 |
20170298795 | AUTOMATIC PURIFYING DEVICE FOR ENGINE EXHAUST GASES - An automatic purifying device for engine exhaust gases is disclosed. Exhaust gases flow through a necked portion to be speeded and the temperature of the exhaust gases is kept uniform after entering an exhaust inlet, and the speeded exhaust gases then pass through a flared mouth so as to be diffused through metal catalyst carriers and a straight-through ceramic filter or wall-flow filter, allowing the poisonous emissions such as nitrogen oxides (NOx) to collide with the metal catalyst carriers to generate high heat to ignite carbon particles, carbon monoxide, hydrocarbons, and the like which are then decomposed and reduced to nitrogen gas and water by added urea or ammonia in the middle of passing through the straight-through ceramic filter or wall-flow filter, where the generated water can then be discharged through a drain port, thereby decreasing pollution to the environment. | 2017-10-19 |
20170298796 | EXHAUST SYSTEM FOR A DIESEL ENGINE - An exhaust system for treating an exhaust gas produced by a diesel engine comprises: (a) an emissions control device (ECD) for oxidising carbon monoxide (CO) and/or hydrocarbons (HCs), wherein the emissions control device comprises a platinum group metal (PGM) and a substrate, wherein the PGM is platinum, palladium or a combination thereof; (b) an injector for introducing an ammonia precursor into the exhaust gas, which is downstream of the ECD; (c) a first selective catalytic reduction (SCR) catalyst downstream of the injector, wherein the first SCR catalyst comprises a substrate and a first SCR composition, wherein the substrate is either a flow-through substrate or a filtering substrate; (d) a second SCR catalyst downstream of the first SCR catalyst, wherein the second SCR catalyst comprises a flow-through substrate and a second SCR composition; and wherein at least one of the ECD and the first SCR reduction catalyst has a filtering substrate. | 2017-10-19 |
20170298797 | EXHAUST GAS PURIFICATION CATALYST - An exhaust gas purification catalyst having an excellent exhaust partition ability while reducing the increase in pressure loss. Exhaust gas purification catalyst includes a substrate having a wall-flow structure with partition wall, upstream coating section formed in portions of partition wall facing entrance cell, from exhaust inlet-side end in the extending direction of partition wall, and downstream coating section formed in portions of partition wall facing exit cell, from exhaust outlet-side end in the extending direction, having a length shorter than the entire length L | 2017-10-19 |
20170298798 | HONEYCOMB STRUCTURE BODY AND METHOD OF DESIGNING HONEYCOMB STRUCTURE BODY - A honeycomb structure body has main cells having a tubular shape and main cell walls. Each main cell is surrounded by the main cell walls. A virtual base structure body has base cell walls and base cells. The honeycomb structure body has an improved structure obtained by modifying a structure of the virtual base structure body. Each base intersecting point, at which base cell walls intersect, is determined by a polar coordinate (r, θ) using a radius vector r and a deflection angle θ. Each main intersecting point is formed on a polar coordinate (r′, θ) using the deflection angle θ and a main radius vector r′ which is obtained by multiplying the radius vector r and a constant magnification without changing the deflection angle θ. A cell density varying section varies its cell density and is formed in at least a part of the honeycomb structure body. | 2017-10-19 |
20170298799 | METHOD AND APPARATUS FOR EXHAUST PURIFICATION FOR AN INTERNAL COMBUSTION ENGINE - An exhaust aftertreatment system for purifying an exhaust gas feedstream that is expelled from an internal combustion engine that is operable at an air/fuel ratio that is lean of stoichiometry is described. The exhaust aftertreatment system includes a barrier discharge plasma reactor that is disposed upstream relative to a catalytic reactor and electrically connected to a plasma controller. The barrier discharge plasma reactor is controlled to generate ozone from constituents of the exhaust gas feedstream when the internal combustion engine is operating at a lean air/fuel ratio and at a low temperature condition. The generated ozone reacts, in the catalytic reactor, to oxidize non-methane hydrocarbons contained in the exhaust gas feedstream when the internal combustion engine is operating at lean air/fuel ratio and at low temperature conditions. | 2017-10-19 |
20170298800 | METHOD AND APPARATUS FOR EXHAUST PURIFICATION FOR AN INTERNAL COMBUSTION ENGINE - An exhaust aftertreatment system for purifying an exhaust gas feedstream expelled from an internal combustion engine that is operable at an air/fuel ratio that is lean of stoichiometry is described. The exhaust aftertreatment system includes a plasma reactor disposed upstream of a selective catalytic reactor device. The plasma reactor is electrically connected to a plasma controller. The plasma controller controls the plasma reactor to generate ozone from constituents of the exhaust gas feedstream, and the ozone reacts to oxidize nitrogen oxide contained in the exhaust gas feedstream to form nitrogen dioxide. The nitrogen dioxide reacts with a reductant in the selective catalytic reactor device to form elemental nitrogen and water. | 2017-10-19 |
20170298801 | METHOD AND SYSTEM FOR EXHAUST PARTICULATE MATTER SENSING - Methods and systems are provided for a particulate matter sensor positioned downstream of a diesel particulate filter in an exhaust system. In one example, a particulate matter sensor may include a spherical assembly including a hollow rod and a plurality of flow tubes connected to diametrically opposite ends of the assembly, and a sensor element positioned within the assembly, distal to the plurality of flow tubes, thus protecting the sensor element from contaminants and water droplets condensing at or near the plurality of flow tubes. In addition, the support rod may further include a drainage hole to flow larger particulates out the spherical assembly and out into the exhaust passage. | 2017-10-19 |
20170298802 | STRUCTURE OF EXHAUST PIPE - A structure of an exhaust pipe may include a first pipe discharging exhaust gas produced in engine cylinders disposed in a first side row, a second pipe discharging exhaust gas produced in engine cylinders disposed in a second side row, a merging pipe having a first end communicatively connected to the first pipe, and a second end communicatively connected to the second pipe, and a valve plate embedded in the merging pipe, and selectively closed or opened. | 2017-10-19 |
20170298803 | EXHAUST DEVICE FOR FOUR-CYLINDER INTERNAL COMBUSTION ENGINE - In an in-line four-cylinder internal combustion engine, exhaust ports ( | 2017-10-19 |
20170298804 | THIN FOIL ENCAPSULATED ASSEMBLIES - An injector tube assembly that includes thin foil insulation around a receiver tube and a relatively rigid housing secured to the thin foil and bearing on tube insulation while also being packed with junction insulation. | 2017-10-19 |
20170298805 | COMBUSTION MACHINE - A combustion machine comprising an internal combustion engine and a cooling system that has a coolant pump, a main cooler, a heating heat exchanger, a bypass which bypasses the heating heat exchanger, coolant ducts in the internal combustion engine, and a regulating device with an actuator which serves for the regulated distribution of a coolant as a function of at least one local coolant temperature. The invention is characterized in that, when the actuator is actuated in one direction, the regulating device —when it is in a first position, allows coolant flow through the internal combustion engine and the heating heat exchanger, and prevents coolant from flowing through the bypass and the main cooler; —when it is in a second position, additionally allows coolant to flow through the bypass; and —when it is in a third position, additionally allows coolant to flow through the main cooler. | 2017-10-19 |
20170298806 | ENGINE COOLANT MONITORING SYSTEM FOR A MACHINE - An engine coolant monitoring system for a machine is disclosed. The engine coolant monitoring system may have a test device configured to test a fluid sample of an engine coolant. The engine coolant monitoring system may also have a database configured to store a test result generated by the test device, the test result including a plurality of characteristics of the fluid sample. In addition, the engine coolant monitoring system may have a controller. The controller may be configured to access a rule-set associated with the engine coolant from the database, the rule-set having criteria associated with the characteristics. The controller may also be configured to label the engine coolant as normal when the characteristics of the fluid sample satisfy the criteria and label the engine coolant as abnormal when the characteristics do not satisfy at least one criterion included in the rule-set. | 2017-10-19 |
20170298807 | LIQUID TEMPERATURE SENSOR - Systems and methods for monitoring the temperature of a liquid are disclosed herein. Systems can include a thermistor in contact with a liquid coolant and circuitry configured to measure a temperature of the thermistor by applying a nominal current through the thermistor and detecting a voltage drop across the thermistor. The circuitry may be further configured to apply a current pulse greater than the nominal current through the thermistor, detect a transient thermistor response to the current pulse, and compare the detected transient thermistor response to an expected transient response. The circuitry may be capable of determining if the thermistor is immersed in a fluid or at least partially located within a fluid-free region based on comparing the detected transient thermistor response to the expected transient response. | 2017-10-19 |
20170298808 | METHOD FOR SPRAYING A FLUID ONTO A CHARGE AIR COOLER OF A MOTOR VEHICLE - A method for spraying a fluid onto a charge air cooler of a motor vehicle includes measuring a first temperature with the aid of a first sensor of the motor vehicle; measuring a second temperature with the aid of a second sensor of the motor vehicle; comparing the first temperature with a first reference temperature by a controller of the motor vehicle; comparing the second temperature with a second reference temperature by the controller of the motor vehicle if the first temperature is higher than the first reference temperature or equal to the first reference temperature; and spraying at least some of the fluid onto the charge air cooler during a spray-on cycle if the second temperature is higher than the second reference temperature or equal to the second reference temperature. | 2017-10-19 |
20170298809 | METHOD AND DEVICE FOR ADJUSTING A CHARGING PRESSURE IN AN INTERNAL COMBUSTION ENGINE BY MEANS OF A PRESSURE-WAVE SUPERCHARGER - The invention relates to a method and to a device for adjusting a charging pressure in an internal combustion engine by means of a pressure-wave supercharger, wherein the pressure-wave supercharger has a cell rotor, which passes through at least two compression cycles per revolution, wherein a high-pressure exhaust-gas flow is divided into a first and a second high-pressure exhaust-gas partial flow, wherein a fresh-air flow and the first high-pressure exhaust-gas partial flow are fed to the cell rotor and a first compressed fresh-air flow and a low-pressure exhaust-gas flow are led away from the cell rotor in the first compression cycle, and wherein the fresh-air flow and the second high-pressure exhaust-gas partial flow are fed to the cell rotor and a second compressed fresh-air flow and the low-pressure exhaust-gas flow are led away from the cell rotor in the second compression cycle, wherein the first and the second compressed fresh-air flow are combined into a charge air, and wherein the charge air is fed to the internal combustion engine, wherein the second high-pressure exhaust-gas partial flow is controlled in order to control the charging pressure of the charge air in such a way, and wherein the second compressed fresh-air flow is led through a check valve before the first and the second compressed fresh-air flow are combined into the charge air. | 2017-10-19 |
20170298810 | Turbocharger Speed Anomaly Detection - A process for monitoring turbocharger operation in a machine is disclosed. The machine includes a power source having an intake manifold for supplying the power source with air and a plurality of turbochargers. Each turbocharger includes an air inlet passageway to receive air, a plurality of pressure sensors arranged within the inlet passageway, a compressor configured to pressurize air, an air outlet passageway to direct pressurized air from the compressor to the intake manifold, and an exhaust turbine operably driven by exhaust gas from the power source and coupled to the compressor by a turbine shaft. The process includes monitoring the differential pressure across the air inlet passageway for each turbocharger, comparing the differential pressures for each turbocharger and indicating an anomaly in turbocharger speed when the differential pressure for one turbocharger exceeds the differential pressure for another turbocharger by a threshold amount. | 2017-10-19 |
20170298811 | METHOD AND SYSTEM FOR COMPRESSOR OUTLET TEMPERATURE REGULATION - Methods and systems are provided for controlling a boosted engine system, having a turbocharger and a charge air cooler, to limit overheating of a compressor outlet. In one example, a method includes predicting an engine torque profile based on current and future engine operating conditions. The method then models a compressor outlet temperature profile and reduces engine torque output to limit overheating of the compressor outlet. | 2017-10-19 |
20170298812 | OVERRUN AIR RECIRCULATION VALVE FOR A COMPRESSOR OF AN INTERNAL COMBUSTION ENGINE - A divert-air valve for a compressor of an internal combustion engine includes a flow housing with a duct, an actuator, a control body moved by the actuator to control a throughflow cross section of the duct, an armature, openings in the control body, a valve housing with a housing wall, a support ring with a ring-shaped plate and a cylinder wall, and a sealing ring which seals the housing interior with respect to a part of the duct. The armature is connected to the control body. The openings fluidically connect the housing interior to a part of the duct. The valve housing surrounds the actuator and a part of the control body. The support ring bears, via the cylinder wall, radially from the outside against the housing wall. The radial sealing ring lies axially against the ring-shaped plate and bears radially at the outside against the housing wall. | 2017-10-19 |
20170298813 | VARIABLE NOZZLE UNIT AND VARIABLE-CAPACITY SUPERCHARGER - A variable nozzle unit in a variable-capacity supercharger includes: a first nozzle ring disposed in a turbine housing and formed with a plurality of first support holes; a second nozzle ring disposed to face the first nozzle ring and formed with a plurality of second support holes that are through-holes corresponding to the first support holes; a plurality of variable nozzles supported rotatably by the first and second nozzle rings; and a plurality of seal members disposed between a turbine scroll channel and a turbine wheel side. The variable nozzles include first nozzle shafts that are rotatably supported by the first support holes, and second nozzle shafts are rotatably supported by the second support holes, and a first seal member included in the plurality of seal members is provided at the turbine wheel side relative to the second support holes. | 2017-10-19 |
20170298814 | SURGE DETERMINATION DEVICE, SURGE DETERMINATION METHOD, AND PROGRAM - This surge determination device is provided with a surge determination unit for determining the presence or absence of a surge of a compressor that outputs compressed air to an engine on the basis of a rotation speed of the engine and an air flow rate. | 2017-10-19 |
20170298815 | INTERNAL COMBUSTION ENGINE - An internal combustion engine provided with a cylinder block which can move relative to a crankcase is provided with a block movement mechanism arranged at just one side of the left and right of the internal combustion engine, a support member supporting a side surface of the cylinder block, and a pushing member pushing against a side surface of the cylinder block at the opposite side to the side surface supported by the support member. Further, the support member supports the side surface of the cylinder block at the side of arrangement of the block movement mechanism, while the pushing member pushes against the side surface of the cylinder block at the opposite side to the side of arrangement of the block movement mechanism. | 2017-10-19 |
20170298816 | GAS TURBINE ENGINE - A gas turbine engine comprises a relatively high pressure compressor coupled to a relatively high pressure turbine by a relatively high pressure shaft; a relatively low pressure compressor coupled to a relatively low pressure turbine by a relatively low pressure shaft rotatable independently of the high pressure shaft; a first combustor located downstream of the high pressure compressor and upstream of the high pressure turbine; and a second combustor located downstream of the high pressure turbine, and upstream of the low pressure turbine. The engine further comprises a coupling arrangement configured to selectively transfer torque between the high pressure shaft and the low pressure shaft. | 2017-10-19 |
20170298817 | COMBUSTOR AND GAS TURBINE ENGINE - Provided is a combustor that has an efficient cooling structure. Also provided is a gas turbine engine that is provided with the combustor. A combustor that is for a gas turbine and that is provided with a combustion liner and with a fuel injection part that is provided to one end of the combustion liner so as to pass through the combustion liner. The combustion liner is provided with an inner liner that forms a combustion chamber inside the combustion liner, with a coolant flow path that is an annular space that is formed outside the inner liner, and with a coolant supply means that supplies hydrogen gas to the coolant flow path. In this combustor, the inner liner that is the combustion chamber is cooled by the hydrogen gas that flows in the coolant flow path. | 2017-10-19 |
20170298818 | SOLAR CHEMICALLY RECUPERATED GAS TURBINE SYSTEM - A solar chemically recuperated gas turbine system includes an exhaust-gas reformer, a solar reformer and a gas turbine unit with a combustion chamber. The reaction outlet of the exhaust-gas reformer is connected to the inlet of the solar reformer, the flue gas side inlet of the exhaust-gas reformer is connected to the exhaust-gas outlet of the gas turbine. The solar reformer outlet is connected to the combustion chamber inlet. Combustion gas drives the gas turbine after fuel burns in the combustion chamber, and the exhaust gas enters the exhaust-gas reformer. Fuel and steam are mixed and enter the reaction side of the exhaust-gas reformer through a fuel inlet. A reforming reaction between the fuel and steam under heating of the exhaust gas generates syngas. A further reforming reaction occurs by absorbing concentrated solar energy after the syngas enters the solar reformer, and the reactant is provided to combustion chamber. | 2017-10-19 |
20170298819 | TURBINE IMPELLER - A turbine impeller supplies a high-pressure fluid through a scroll flow route and/or a exhaust supply port of a fixed nozzle and includes: blade components converting the fluid into a rotational force; and a rotor, configured with the blade components and can rotate around a specified rotational axis, wherein a direction, relative to a gas relative inflow velocity of the rotor, specified by using the fluid supply port as a starting point and subtracting a rotational velocity component of the rotor from a supply velocity component of the fluid is set to not intersect with the rotational axis of the rotor; and a shape, from a halfway portion to a front edge portion, of the blade component inclines, relative to a direction from a center of the rotor to an upstream portion of the blade component, toward front side of a rotating direction of the rotor by a specified angle. | 2017-10-19 |
20170298820 | A HEAT RECOVERY UNIT AND POWER PLANT - A heat recovery unit for generating a heated fluid by a hot exhaust gas includes a housing having an inlet for introducing hot exhaust gas and an outlet for discharging treated exhaust gas, and arranged in the housing at least one heat exchanger for heat exchange between the hot exhaust gas and a fluid, and an auxiliary combustor for combusting fuel with hot exhaust gas. The auxiliary combustor is provided with a fuel supply, which auxiliary combustor is arranged downstream of the at least one heat exchanger in the housing. An exhaust gas bypass for a part of the hot exhaust gas is provided, having an inlet for exhaust gas, and being positioned upstream of the at least one heat exchanger, and having an outlet in direct fluid communication with the auxiliary combustor. | 2017-10-19 |
20170298821 | SHORT INLET WITH INTEGRATED LINER ANTI-ICING - A nacelle for a gas turbine engine, the nacelle includes an inlet axially forward of a fan section. The inlet includes an interior surface. A leading edge includes an inlet cavity. A first conduit communicates airflow to the inlet cavity for preventing accretion of ice on the leading edge. An inlet duct is open to the interior surface aft of the inlet cavity. A second conduit is in fluid communication with the first conduit and the inlet duct. The second conduit communicates airflow to the inlet duct for generating film heating airflow over the interior surface for preventing ice accretion. A gas turbine engine is also disclosed. | 2017-10-19 |
20170298822 | GAS TURBINE ENGINE FOR AN AIRCRAFT - A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber. | 2017-10-19 |
20170298823 | COOLED COMPONENT - A cooled gas turbine engine component includes a wall having a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface. Each aperture includes an inlet portion, a collection chamber, a metering portion, a U-shaped bend portion and a diffusing portion arranged in flow series from the inlet to the outlet. The inlet portion of each aperture is arranged substantially perpendicularly to a surface of the collection chamber. The metering portion of each aperture is arranged to extend longitudinally from a first lateral side of the collection chamber and the diffusing portion of each aperture is arranged at an angle to the second surface. Each outlet has a quadrilateral shape in the second surface of the wall and each outlet is displaced laterally from the metering portion. | 2017-10-19 |
20170298824 | Gas-turbine combustion chamber with impingement-cooled bolts of the combustionchamber tiles - The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall, to which combustion chamber tiles are fastened by means of bolts, where in the bolt fastening area in the combustion chamber wall at least one impingement cooling hole is provided, the center axis of which is inclined to the center axis of the bolt and intersects a transition area between the bolt and the combustion chamber tile. | 2017-10-19 |
20170298825 | Cooling Air Architecture for Compact Size and Performance Improvement - A gas turbine engine has a fan and a compressor section with a first lower pressure location and a second higher pressure location. A heat exchanger and a higher pressure tap from the second higher pressure location pass through the heat exchanger. Air in the higher pressure tap is cooled by air from a lower pressure tap from the first lower pressure location. A valve controls flow to the heat exchanger from the lower pressure tap, the valve being controlled to limit flow from the lower pressure tap under certain conditions. | 2017-10-19 |
20170298826 | Industrial gas turbine engine with turbine airfoil cooling - A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines. | 2017-10-19 |
20170298827 | Segmented Annular Combustion System - An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner including an inner band radially spaced from an outer band and an inner flow annulus formed therebetween, and an outer liner radially spaced from the inner liner and comprising an inner band radially spaced from an outer band and an outer flow annulus formed therebetween. The fuel nozzle is positioned radially between the inner liner and the outer liner, and the panel fuel injector extends radially between the inner liner and the outer liner. At least one of the inner flow passage and the outer flow passage is in fluid communication with at least one of a premix air plenum, a cooling air cavity and a cooling air plenum defined within the panel fuel injector. | 2017-10-19 |