04th week of 2020 patent applcation highlights part 28 |
Patent application number | Title | Published |
20200025006 | NON-CONTACT SEAL WITH RESILIENT BIASING ELEMENT(S) - A seal device includes a plurality of seal shoes, a seal base, a plurality of spring elements and a resilient biasing element. The seal shoes are arranged around an axis. The seal base circumscribes the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam connects the first mount to the second mount. The resilient biasing element is radially between and engaged with first and second components of the seal device, where the first component is configured as or otherwise includes the first mount or the second mount. | 2020-01-23 |
20200025007 | SEAL ASSEMBLY FOR TURBINE ENGINE COMPONENT - A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing mountable to an engine static structure, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier. The wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing. The wedge seal is separate and distinct from the seal carrier. A method of sealing between adjacent components of a gas turbine engine is also disclosed. | 2020-01-23 |
20200025008 | SEAL ASSEMBLY FOR SEALING AN AXIAL GAP BETWEEN COMPONENTS - A seal assembly extends along an axis and seals an axial (and/or radial) gap between a first component and a second component. The seal assembly includes a seal carrier and a seal element. The seal element extends axially (and/or radially) between a first portion and a second portion. The first portion of the seal element is slidingly arranged within a slot in an axial end (or a radial side) of the seal carrier. The second portion of the seal element is configured to axially (and/or radially) engage the second component. | 2020-01-23 |
20200025009 | Airfoil Fluid Curtain to Mitigate or Prevent Flow Path Leakage - Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes combustor and turbine portions that are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils that each have an inner end radially opposite an outer end and define an internal cavity for receipt of a flow of cooling fluid. The inner end of each nozzle airfoil is received in one of the plurality of inner wall pockets and defines an outlet for the flow of cooling fluid to flow from the internal cavity to the pocket, which forms a fluid curtain to discourage fluid leakage from the flow path. | 2020-01-23 |
20200025010 | Seal Assembly for Counter Rotating Turbine Assembly - The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion. | 2020-01-23 |
20200025011 | BLADE OUTER AIR SEAL AFT HOOK RETAINER - A gas turbine engine includes a turbine section including at least one turbine rotor having at least one blade. A blade outer air seal is positioned radially outward of a radially outer tip of the at least one turbine blade. The blade outer air seal has a forward hook and an aft hook. The forward hook is supported on a forward retainer and the aft hook is supported on an aft hook retainer. The aft hook retainer provides structure to prevent rotation of the blade outer air seal relative to the aft hook retainer. There is an interference fit between the aft hook retainer and the forward retainer. A load path is provided from a static structure through the aft hook retainer to the forward retainer. | 2020-01-23 |
20200025012 | TURBINE SHROUD HAVING CERAMIC MATRIX COMPOSITE SEAL SEGMENT - A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine. | 2020-01-23 |
20200025013 | TURBINE SHROUD SEGMENT WITH LOAD DISTRIBUTION SPRINGS - A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine. | 2020-01-23 |
20200025014 | SEAL COATING - A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event. | 2020-01-23 |
20200025015 | TURBINE SHROUD SEGMENT WITH SIDE PERIMETER SEAL - A turbine shroud segment of a turbine shroud for use in a turbine of a gas turbine engine is disclosed herein. The turbine shroud segment includes a carrier segment and a blade track segment. The carrier segment includes metallic materials. The blade track segment includes ceramic matrix composite materials. A seal is arranged between the carrier segment and the blade track segment. | 2020-01-23 |
20200025016 | COATING TO IMPROVE OXIDATION AND CORROSION RESISTANCE OF ABRASIVE TIP SYSTEM - An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degree Fahrenheit, comprising: a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material. | 2020-01-23 |
20200025017 | METHOD FOR MANUFACTURING AN ANNULAR CASING EQUIPPING A TURBOMACHINE - The invention relates to a method for manufacturing a carrying casing ( | 2020-01-23 |
20200025018 | MODULE FOR A TURBOMACHINE - The present invention relates to a module for a turbomachine. The guide vane arrangement has a guide vane, an inner platform, and a first guide pin, the guide vane is arranged radially outside on the inner platform and the first guide pin is arranged radially inside on the inner platform, and wherein the seal carrier is arranged radially inside the inner platform and forms an uptake, which is open radially outward, the first guide pin of the guide vane arrangement being arranged in the uptake. In the uptake, a slide body is arranged, on which the first guide pin of the guide vane arrangement, with respect to a rotation around the longitudinal axis of the module, finds a contact and is guided in a radially movable manner in this contact. The slide body is formed in one piece with a wall of the seal carrier, which axially bounds the uptake. | 2020-01-23 |
20200025019 | SYSTEMS AND METHODS FOR CONTROLLING BLADE TIP CLEARANCES - A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system. | 2020-01-23 |
20200025020 | GAS TURBINE ENGINE RAMPED RAPID RESPONSE CLEARANCE CONTROL SYSTEM - An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies. | 2020-01-23 |
20200025021 | ROD ASSEMBLY AND TURBOCHARGER - A rod assembly includes a turnbuckle that extends along a central axis, a first rod that is to be screwed into a first adjustment hole of the turnbuckle, a second rod that is to be screwed into a second adjustment hole of the turnbuckle, a first nut that is fitted to a first adjustment end portion of the first rod, and a second nut that is fitted to a second adjustment end portion of the second rod. A first turnbuckle-welded portion is provided between the first nut and the turnbuckle, and a second turnbuckle-welded portion is provided between the second nut and the turnbuckle. A first rod-welded portion is provided between the first nut and the first rod, and a second rod-welded portion is provided between the second nut and the second rod. | 2020-01-23 |
20200025022 | DUAL-MODE PLUG NOZZLE - A method for controlling flow through an exhaust nozzle includes: providing a centerbody including a maximum diameter section; providing an inner shroud surrounding the centerbody, including at least a middle section of decreased diameter and terminating at an aft edge; providing an outer shroud. wherein the centerbody and the inner shroud collectively define a throat, and the outer shroud and the centerbody collectively define an exit; selectively translating the inner shroud and outer shroud to vary the throat; and selectively translating the outer shroud to vary the ratio of the exit to the throat; wherein, when the inner shroud is in a forward position, its aft edge is forward of the maximum diameter section of the centerbody, such that the throat of the nozzle is formed between the aft edge of the inner shroud and the centerbody. | 2020-01-23 |
20200025023 | CAM ISOLATION SYSTEM FOR GAS TURBINE ENGINE COMPRESSOR SECTION - A cam isolation system for a gas turbine engine compressor actuator includes a torque tube. The system also includes a cam bracket operatively coupled to an engine case structure, the cam bracket defining a slot. The system further includes an actuator bracket operatively coupled to the torque tube at a first end of the actuator bracket, the actuator bracket having a pin disposed within the slot of the cam bracket. | 2020-01-23 |
20200025024 | AIRCRAFT TURBOMACHINE COMPRISING DECOUPLING MEANS - An aircraft turbomachine ( | 2020-01-23 |
20200025025 | TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS - A turbine vane assembly adapted for use in a gas turbine engine includes a vane support and a vane heat shield comprising ceramic matrix composite materials to insulate the metallic materials of the vane support. The turbine vane assembly further includes an aero-load transfer rib located outside of a primary gas path and configured to carry loads applied to the vane heat shield to the vane support. | 2020-01-23 |
20200025026 | TURBINE SHROUD INCLUDING PLURALITY OF COOLING PASSAGES - Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage. | 2020-01-23 |
20200025027 | BLADE OUTER AIR SEAL COOLING SCHEME - A cooling scheme for a blade outer air seal includes a perimeter cooling arrangement configured to convectively cool a perimeter of the blade outer air seal, and a core cooling arrangement configured to cool a central portion of the blade outer air seal through impingement cooling and to provide film cooling to an inner diameter face of the blade outer air seal. | 2020-01-23 |
20200025028 | ATTACHMENT BLOCK FOR BLADE OUTER AIR SEAL PROVIDING IMPINGEMENT COOLING - A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a central chamber within the attachment block, and communicates with cooling holes through a radially inner face of the attachment block to direct cooling air at the central web of the blade outer air seal. A blade outer air seal is also disclosed. | 2020-01-23 |
20200025029 | ATTACHMENT BLOCK FOR BLADE OUTER AIR SEAL PROVIDING CONVECTION COOLING - A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed. | 2020-01-23 |
20200025030 | GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION - A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing. | 2020-01-23 |
20200025031 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine includes a fan shaft that drives a fan that has fan blades. A fan shaft support that supports the fan shaft defines a fan shaft support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness and less than 8% of the gear mesh transverse stiffness. | 2020-01-23 |
20200025032 | 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 supports the fan shaft and defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness. | 2020-01-23 |
20200025033 | GAS TURBINE ENGINE AND OIL SYSTEM THEREOF - A gas turbine engine for an aircraft comprises: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a core casing surrounding the engine core. The gas turbine engine further comprises a core cowl surrounding the engine core and the core casing. The gas turbine engine further comprises an engine accessory gearbox driven by a take-off from the core shaft. The gas turbine engine further comprises an oil system having one or more oil pumps powered by the engine accessory gearbox for circulating lubricating oil around components of the engine including the engine accessory gearbox, and having an oil tank for receiving and storing oil scavenged from the engine components before recirculation thereto. The gas turbine engine further comprises an oil fill line which extends from the engine accessory gearbox to an inlet port accessible from the core cowl, the oil tank being fillable from the inlet port via the fill line and the engine accessory gearbox. | 2020-01-23 |
20200025034 | FAN CASE WITH INTERLEAVED LAYERS - A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture. | 2020-01-23 |
20200025035 | GAS TURBINE ENGINE KEEL BEAM - A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct. | 2020-01-23 |
20200025036 | LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE - According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40. | 2020-01-23 |
20200025037 | TURBINE DISTRIBUTOR SECTOR FOR AN AIRCRAFT TURBINE ENGINE - Turbine distributor sector for an aircraft turbine engine, including an external annular platform sector and an internal annular platform sector, the sectors being coaxial and being connected together by blade assemblies including inner cavities cooled by gas circulation, the external platform sector including through openings of which radially internal ends open into the inner cavities, wherein the external platform sector includes inner ducts for supplying the cavities with gas, the ducts including air outlets opening into the openings and air inlets opening onto a portion of the external annular surface of the external platform sector. | 2020-01-23 |
20200025038 | SEALING CONFIGURATION TO REDUCE AIR LEAKAGE - A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a boot seal configured to surround a length of the fluid transfer tube, the boot seal having a first end and a second end and a seal ring disposed at the first end, an attachment ring configured to mate with the seal ring and to secure the seal ring against a casing, an annular ring configured to mate with an interior surface of the boot seal at the second end and to surround a portion of the fluid transfer tube, and a clamp ring configured to surround the second end of the boot seal proximate the annular ring. | 2020-01-23 |
20200025039 | SERVICE APPARATUS FOR USE WITH ROTARY MACHINES - A service apparatus for use in maintaining a machine including a stator and a rotor is provided. The service apparatus includes a carriage assembly configured to couple to the rotor. The service apparatus is selectively transitionable between a stowed position in which the service apparatus is rotatable with the rotor and an extended position in which the service apparatus is extended toward the stator. The service apparatus also includes at least one maintenance device coupled to the carriage assembly. The at least one maintenance device is operable to perform a maintenance operation on a surface of the stator with the service apparatus in the extended position. | 2020-01-23 |
20200025040 | TOOL FOR FIXING AN OUTER COLLAR OF AN INTERMEDIATE CASING OF A TURBOMACHINE - The present disclosure provides a tool for fixing an outer collar to a unit having at least one inner hub and a plurality of vanes. The tool includes a connecting interface with a lifting system and an attachment interface for the outer collar. The attachment interface includes a support surface configured to be supported on one face of a flange of the outer collar, a centering surface configured to be inserted into a hole of the flange, and at least one attachment element configured to attach the outer collar. The tool further includes a surface for centering the tool with respect to the unit, a surface for supporting the tool on the unit, and an actuator for adjusting the support surface with respect to the attachment interface. | 2020-01-23 |
20200025041 | NECKED DEBRIS SEPARATOR FOR A GAS TURBINE ENGINE - A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis. | 2020-01-23 |
20200025042 | Variable Pressure Inventory Control of Closed Cycle System with a High Pressure Tank and an Intermediate Pressure Tank - Systems and methods for variable pressure inventory control of a closed thermodynamic cycle power generation system or energy storage system, such as a reversible Brayton cycle system, with at least a high pressure tank and an intermediate pressure tank are disclosed. Operational parameters of the system such as working fluid pressure, turbine torque, turbine RPM, generator torque, generator RPM, and current, voltage, phase, frequency, and/or quantity of electrical power generated and/or distributed by the generator may be the basis for controlling a quantity of working fluid that circulates through a closed cycle fluid path of the system. | 2020-01-23 |
20200025043 | MODULE OF A VARIABLE VALVE DRIVE OF AN INTERNAL COMBUSTION ENGINE - A module of a variable valve drive of an internal combustion engine is proposed that includes a push rod mounted longitudinally in a cylinder head of the internal combustion engine. The push rod is actuated by a linear actuator that includes an armature that makes contact, at least indirectly with the push rod, to displace it in a first longitudinal direction. A switchable rocker arm with a coupling slide arranged transversely to a longitudinal extent or side of the rocker arm corresponds to an actuating finger that extends from the push rod. The coupling slide includes a slide part that projects laterally from the rocker arm and can be acted upon by a free end of the actuating finger. Kinetic energy of the push rod is dissipated or converted at least partially via a separate damper in the first longitudinal direction before it reaches a final position. | 2020-01-23 |
20200025044 | HYDROSTATIC CAMSHAFT PHASER - A hydrostatic camshaft phaser system includes a hydraulically-actuated camshaft phaser with a rotor; and a stator housing that receives the rotor and includes an advancing chamber and a retarding chamber defined at least partially by the vane; and a variable displacement pump, in fluid communication with the hydraulically-actuated camshaft phaser, comprising a first chamber in fluid communication with the advancing chamber and a second chamber in fluid communication with the retarding chamber; the first chamber receives fluid from a first non-continuous groove extending along a camshaft surface or a bearing surface and the second chamber receives fluid from a second non-continuous groove extending along the camshaft surface or the bearing surface during a first portion of camshaft rotation, and the first chamber receives fluid from the second non-continuous groove and the second chamber receives fluid from the first non-continuous groove during a second portion of camshaft rotation. | 2020-01-23 |
20200025045 | TAPPET - Provided is a tappet capable of supplying lubricating oil to a cam even when provided with a lash adjuster. | 2020-01-23 |
20200025046 | Oil Pan - An oil pan disposed underneath an engine of a motorcycle and configured to reserve engine oil includes a shallow bottom portion and a deep bottom portion formed to extend in a front-rear direction of the motorcycle substantially at a center in a left-right direction of the motorcycle of the shallow bottom portion, and to become deeper than the shallow bottom portion, and in which a space defined in the left-right direction of the motorcycle between both side wall portions of the deep bottom portion that face each other in the left-right direction of the motorcycle is formed to increase as the deep bottom portion extends from a front toward a rear thereof with respect to the motorcycle. | 2020-01-23 |
20200025047 | INTERNAL COMBUSTION ENGINE - There is provided an internal combustion engine in which oil can be kept in an oil passageway when oil is supplied, so that the time required to supply oil can be reduced. In an internal combustion engine in which an oil supply inlet for replenishing, with oil, an oil pan reservoir chamber disposed in a lower portion of a crankcase extends obliquely downwardly from an oil supply port at an upper end thereof, the oil pan reservoir chamber has an oil pan inlet port disposed in a position offset from a vertical plane, including the oblique oil supply inlet, and a horizontal oil supply passageway bent and extending substantially horizontally from a lower end of the oil supply inlet is connected to the oil pan inlet port. | 2020-01-23 |
20200025048 | BREATHER STRUCTURE OF ENGINE - The disclosure prevents oil separated from blow-by gas by using a breather chamber and discharged to a valve chamber from leaking to the outside from a breather chamber mounting surface between the breather chamber and the valve chamber. A breather chamber includes cylindrical drain passages communicating with a valve chamber, and tips of the drain passages exceed breather chamber mounting surfaces of a cylinder head and a head cover and protrude from opening parts toward a side of the valve chamber, so the oil separated from the blow-by gas in the breather chamber can be reliably discharged to the valve chamber and prevented from leaking to the outside from the breather chamber mounting surfaces. | 2020-01-23 |
20200025049 | ACTUATOR DEVICE - The present invention relates to an actuator device configured for impelling elements between two positions such that, in the end position with maximum extension, the force being applied is limited, preventing the impelled element from becoming damaged. | 2020-01-23 |
20200025050 | SEPARATELY DETERMINING FIRING DENSITY AND PUMPING DENSITY DURING FIRING DENSITY TRANSITIONS FOR A LEAN-BURN INTERNAL COMBUSTION ENGINE - A skip fire engine controller and method of control is described wherein during transitions from a first firing density to a second firing density, a firing density and a pumping density are separately set so as to balance the conflicting demands of (a) torque control, (b) Noise, Vibration and Harshness (NVH), (c) air flow through the engine and (d) air-fuel ratio. | 2020-01-23 |
20200025051 | DIESEL OXIDATION CATALYST CONTAINING MANGANESE - The present invention relates to a diesel oxidation catalyst, which comprises a carrier body having a length L extending between a first end face a and a second end face b and a catalytically active material zone A arranged on the carrier body, wherein the material zone A contains palladium and platinum on a manganese-containing carrier oxide, wherein the carrier oxide consists of a carrier oxide component A and a carrier oxide component B and the carrier oxide component B consists of manganese and/or a manganese compound and is present in an amount of 5 to 15 wt. %, calculated as MnO | 2020-01-23 |
20200025052 | HEATING MODULE - A heating module for heating a fluid in a tank of a motor vehicle, a heating module arrangement that includes at least two heating modules, and a tank device having a heating module arrangement. The heating module includes a heating element having a heating element carrier and at least one heating wire arranged on the heating element carrier, and a carrier module which surrounds and supports the heating element at both sides of the heating element carrier, the carrier module having an open support structure so that there is no material arranged between the at least one heating wire and an outer side of the heating module. | 2020-01-23 |
20200025053 | THERMOELECTRIC HEAT ENERGY RECOVERY MODULE GENERATOR FOR APPLICATION IN A STIRLING-ELECTRIC HYBRID AUTOMOBILE - A vehicle is provided which includes a Stirling Cycle engine that generates a flow of exhaust gases from the external combustion of a fuel supply. The vehicle is equipped with a thermoelectric generator module which is in fluidic communication with the flow of exhaust gases generated by the Stirling Cycle engine. The thermoelectric generator module includes a thermopile array, and generates electrical energy from the thermal energy in the flow of exhaust gases. | 2020-01-23 |
20200025054 | SYSTEMS AND METHODS FOR DETERMINING DIFFERENTIAL AND RELATIVE PRESSURE USING A CONTROLLER - An aftertreatment system comprises a housing defining an internal volume. A filter is disposed in the housing and configured to remove particulate matter included in the exhaust gas. A delta pressure sensor configured to measure an inlet apparent pressure value upstream of the filter. An ambient pressure sensor separate from the delta pressure sensor is configured to measure an ambient pressure value of an ambient environment in which the aftertreatment system is located. A controller is configured to receive the inlet apparent pressure value, receive the ambient pressure value from the ambient pressure sensor, determine a relative inlet exhaust pressure value based upon the inlet apparent pressure value and the ambient pressure value, and adjust an exhaust flow rate of the exhaust gas based at least on the relative inlet exhaust pressure value. | 2020-01-23 |
20200025055 | METHOD AND SYSTEM FOR DETERMINING A QUANTITY OF LIQUID IN A TANK - It is proposed a method for determining a quantity of a liquid in a tank, the tank comprising: a first ultrasound subsystem capable of measuring level of liquid present above a predetermined threshold level within the tank; and at least one second ultrasound subsystem, said second ultrasound subsystem being associated with a sensing area within the tank and being configured to measure a parameter characteristic of the liquid, said sensing area being located below the predetermined threshold level. The method comprises in the steps of: checking the validity of the measurement performed by said first ultrasound subsystem (S | 2020-01-23 |
20200025056 | METHOD AND SYSTEM FOR IMPROVING DIAGNOSIS OF A CATALYST - Methods and systems are provided for diagnosing operation of a catalyst in the presence of oxygen sensor degradation over a vehicle life cycle. The methods and systems described herein filter the output of one oxygen sensor according to a time constant of a different oxygen sensor so that determination of a catalyst index ratio is compensated for oxygen sensor degradation. | 2020-01-23 |
20200025057 | Reduced Length Exhaust System With Valve - An exhaust system for receiving exhaust gas from an engine of a vehicle includes first, second, and third exhaust components, and first and second pipes. The first and second exhaust components are each adapted to receive exhaust gas from the engine. The first pipe has a first inlet, and first and second outlets. The first inlet is adapted to receive exhaust gas from the first exhaust component. The second pipe has a second inlet, and third and fourth outlets. The second inlet is adapted to receive exhaust gas from the second exhaust component. The third exhaust component is disposed downstream of and laterally between the first and second exhaust components. The third exhaust component has third and fourth inlets, and fifth and sixth outlets. The third inlet is fluidly connected to the first outlet. The fourth inlet is fluidly connected to the third outlet. | 2020-01-23 |
20200025058 | Power System Radiators and Power Systems Having Radiators - Power system radiators and power systems having radiators are disclosed. An example power system includes: an engine; a generator configured to generate electrical power from mechanical power provided by the engine; power conversion circuitry configured to convert the electrical power from the generator to welding-type power; and a housing enclosing the engine, the generator, and the power conversion circuitry; and a radiator assembly configured to cool the engine and comprising a heat exchanger oriented substantially horizontally when the power system is installed. | 2020-01-23 |
20200025059 | VEHICLE HAVING AN INTEGRATED COOLANT CONTROL VALVE AND A CONTROL METHOD FOR SAME - A control method for a vehicle, provided with an integrated coolant control valve, includes; performing, by a controller, a fault diagnosis of the integrated coolant control valve; determining, by the controller, whether a position sensor is faulty, the position sensor measuring a position of a cam and outputting a corresponding position output when the controller determines that the integrated coolant control valve is faulty; moving the cam for opening and closing a plurality of valves to a maximum position by operating the integrated coolant control valve when the controller determines that the position sensor is faulty; stopping the operation of the integrated coolant control valve by the controller; and limiting a torque output of an engine by the control of the controller according to the position of the cam. | 2020-01-23 |
20200025060 | Fuel Injector and Nozzle Passages Therefor - A fuel injector for an internal combustion engine. The fuel injector has a needle and a nozzle that inter-relate with each other in assembly. Relative movement between the needle and nozzle bring the fuel injector between a closed state of operation and an open state of operation amid use of the fuel injector. The nozzle has one or more passages therein through which fuel is discharged. | 2020-01-23 |
20200025061 | CHARGING DEVICE WITH A WASTEGATE VALVE DEVICE - A charging device may include a turbine housing and a wastegate valve device. The wastegate valve device may include a flap, a spindle arm, a wastegate spindle, an axial stop, and a lever arm non-rotatably attached to the wastegate spindle. The wastegate spindle may be rotatably mounted in a bushing disposed on the turbine housing. A wastegate duct may be disposed in the turbine housing. The wastegate duct may have a duct aperture enclosed by a valve seat. The duct aperture, when in a closed state, may be closed by the flap of the wastegate valve device. A sealing face of the flap may be defined by a sequence of at least two conical peripheral surfaces arranged next to one another and each having a different inclination. | 2020-01-23 |
20200025062 | OXY-HYDROGEN GAS FUEL SYSTEM - An oxy-hydrogen fuel system includes a fluid vessel partially filled with distilled water with graphene powder in the distilled water. A fluid pump is connected to the fluid vessel in a closed loop recirculation to recirculate the distilled water and suspend the graphene powder in the distilled water. A pair of electrodes located in the interior of the fluid vessel and submerged in the distilled water. An electrical power source is operatively connected to the pair of electrodes to generate oxy-hydrogen gas by electrolysis of the distilled water. | 2020-01-23 |
20200025063 | ROTARY PISTON ENGINE - Each of recesses in outer circumferential surfaces of rotors includes: a leading-side area extending forward from a longitudinal center of an associated one of the outer circumferential surfaces in a rotation direction of the rotor, and a trailing-side area continuous with the leading-side area, and extending rearward from the longitudinal center in the rotation direction. From the longitudinal center of the associated one of the outer circumferential surfaces in the rotation direction, forward extension of the leading-side area is longer than rearward extension of the trailing-side area. The leading-side area has a larger volume than the trailing-side area. | 2020-01-23 |
20200025064 | FUEL IGNITION METHODS FOR OPPOSED PISTON ENGINES AND RELATED STRUCTURES - Fuel is ignited in an opposed-piston engine by the mating of unique protruding and recessed portions of opposed pistons. | 2020-01-23 |
20200025065 | BRACKET - A bracket includes: a fastener fixed to an engine by a fastening member; and a protector that is disposed between a high-pressure fuel pump (fuel system component) and a vehicle body frame (vehicle body component) opposed to the high-pressure fuel pump, and covers the high-pressure fuel pump continuously from the fastener. The protector includes: an inclined section that is located more upward at a position further in a direction away from the vehicle body frame; and a curved surface section that is curved between the fastener and the inclined section. | 2020-01-23 |
20200025066 | APPARATUS FOR A GAS TURBINE ENGINE - Apparatus for a gas turbine engine, the apparatus comprising: a low pressure compressor; a high pressure compressor; a first electrical machine configured to provide torque to the low pressure compressor; a second electrical machine configured to receive torque from the high pressure compressor; and wherein the high pressure compressor does not comprise a sub-idle bleed valve. | 2020-01-23 |
20200025067 | GAS TURBINE ENGINE CONFIGURED FOR MODULAR ASSEMBLY/DISASSEMBLY AND METHOD FOR SAME - A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine. | 2020-01-23 |
20200025068 | GEARED ARCHITECTURE GAS TURBINE ENGINE WITH OIL SCAVENGE - A gas turbine engine includes a geared architecture with a multiple of intermediate gears, and a baffle with an oil scavenge scoop adjacent to each of the multiple of intermediate gears. A geared architecture and method are also disclosed. | 2020-01-23 |
20200025069 | GEARED TURBOFAN ARRANGEMENT WITH CORE SPLIT POWER RATIO - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan having a plurality of fan blades, and a nacelle surrounding the plurality of fan blades, a compressor section including a low pressure compressor and a high pressure compressor, the low pressure compressor including a plurality of stages, and the high pressure compressor including 6 or more stages. A turbine section includes a fan drive turbine that drives the fan section through a gear arrangement, and including a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor, the power ratio defined by the second power input divided by the first power input, and the power ratio is less than or equal to 1.0 | 2020-01-23 |
20200025070 | GAS TURBINE ENGINE ARCHITECTURE WITH NESTED CONCENTRIC COMBUSTOR - A gas turbine engine includes an inner annular combustor radially inboard of an outer annular combustor. An outer variable turbine vane array is downstream of the outer annular combustor and an inner variable turbine vane array downstream of the inner annular combustor. | 2020-01-23 |
20200025071 | OFFSET CORES FOR GAS TURBINE ENGINES - A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine. | 2020-01-23 |
20200025072 | ANTI-ICE SYSTEM EXHAUST AIR DISRUPTOR - An airflow disruptor for a gas turbine engine bleed air exhaust port employs a disruptor plate rotatably mounted upstream from an exhaust port of an exhaust duct. An actuator is coupled to the disruptor plate and adapted to rotate the disruptor plate into an external airflow responsive to temperature of exhaust flow in the exhaust port whereby the external airflow is turbulated upstream of the exhaust port. | 2020-01-23 |
20200025073 | GAS TURBINE ENGINE COMPRESSOR CONTROL METHOD - A method of operating a gas turbine engine compressor. The engine comprises a compressor having an environmental control system bleed port having an outlet in fluid communication with an aircraft environmental control system air duct, and an air turbine starter configured to rotate a compressor shaft of the gas turbine engine. The air turbine starter has an inlet in fluid communication with the environmental control system air duct via an air turbine valve. The method comprises determining a surge margin of the compressor, and where the surge margin of the compressor is determined to be below a predetermined minimum surge margin, opening the air turbine valve to supply air to the air turbine. | 2020-01-23 |
20200025074 | AIR SUPPLY SYSTEM FOR AN AIRCRAFT - An air supply system for a gas turbine engine including a first duct which is connected or capable of being connected to a first compressor bleed air supply of a gas turbine engine; a second duct which downstream of the first compressor bleed air supply is connected or capable of being connected to a second compressor bleed air supply of the gas turbine engine; a nozzle by way of which air from the second duct is capable of being blown into the first duct; and an exhaust air duct having an opening which downstream of the nozzle is disposed in the first duct in such a manner that air blown by way of the nozzle into the first duct can flow out of the first duct through the opening into the exhaust air duct. A gas turbine engine and an aircraft are furthermore provided. | 2020-01-23 |
20200025075 | Turbocharger And Drive System With Fuel Cell And Turbocharger - A turbocharger, with a turbine for expanding a first medium having a turbine housing and a turbine rotor, a compressor for compressing a second medium utilising energy extracted in the turbine during expansion of the first medium having a compressor housing and a compressor rotor. A temperature of the first medium that is to be expanded or is expanded is lower than a temperature of the second medium that is to be compressed or is compressed. The turbine rotor and the compressor rotor are directly connected to one another. | 2020-01-23 |
20200025076 | Modular Thermal Storage - A power generation system comprising a shared hot side thermal store, a shared cold side thermal store, a plurality of power subunits, and an electrical bus is disclosed. Each of the power subunits may connected or isolated from the shared hot side thermal store and/or the shared cold side thermal store. | 2020-01-23 |
20200025077 | STATOR CONFIGURATION FOR GAS TURBINE ENGINE - A stator configuration for a gas turbine engine including a splitter segment. Also included is a first stator extending radially outwardly from the splitter segment. Further included is a second stator extending radially inwardly from the splitter segment, the splitter segment, the first stator and the second stator being a single, integrally formed structure. | 2020-01-23 |
20200025078 | GAS TURBINE ENGINE - A gas turbine engine comprising: an engine core comprising a compressor; a compressor bleed valve in communication with the compressor and configured to release bleed air from the compressor; at least one component provided at the inlet of the engine core having a de-icing conduit, configured to receive the bleed air; and a flow controller, configured to provide bleed air to the de-icing conduit of the at least one component in response to either or both of a requirement to de-ice the component and a requirement to release bleed air from the compressor to optimise operation of the core. | 2020-01-23 |
20200025079 | PARTICLE SEPARATOR - An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine. | 2020-01-23 |
20200025080 | DIVERSION OF FAN AIR TO PROVIDE COOLING AIR FOR GAS TURBINE ENGINE - A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages. | 2020-01-23 |
20200025081 | SYSTEMS AND METHODS FOR COOLING ELECTRONIC ENGINE CONTROL DEVICES - A pump for a fuel system include a housing, a pumping element, and a takeoff. The housing has an inlet, an outlet, and channel connecting the inlet to the outlet. The pumping element is supported within the housing and bounds the channel. The takeoff is connected to the housing and is in fluid communication with the channel at a location downstream of the inlet, and upstream of the outlet, to divert partially pressurized fuel for cooling an electronic device. Fuel systems and methods of cooling electronic devices are also described. | 2020-01-23 |
20200025082 | COMPRESSED GAS INTEGRATED POWER AND THERMAL MANAGEMENT SYSTEM - Systems and methods are provided that use compressed gas to power a turbine, which in turn powers a generator, where an expansion of the compressed gas provides cooling for an electrical load that is powered by the generator. | 2020-01-23 |
20200025083 | APPARATUS AND METHOD FOR MITIGATING AIRFLOW SEPARATION AROUND ENGINE COMBUSTOR - According to one embodiment, a gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, the first component including a cooling hole extending from the second surface to the first surface through the first component, wherein the second surface of the first component is oriented relative to a first airflow path such that airflow in the first airflow path separates from the second surface of the first component; and a first fairing secured to the first component proximate the second surface of the first component, the first fairing being configured to redirect airflow in the first airflow path such that the airflow exits the first fairing oriented parallel with the second surface of the first component. | 2020-01-23 |
20200025084 | MICROCHANNEL HEAT EXCHANGERS FOR GAS TURBINE INTERCOOLING AND CONDENSING - A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer. | 2020-01-23 |
20200025085 | Method of Manufacturing Conductive Film Holes - A method for applying a coating to a substrate having a plurality of holes. The method comprises: applying a braze material to a substrate having a plurality of holes; heating the substrate to melt the braze material to form a melt; cooling the substrate to solidify the melt to form plugs in the respective holes; applying a coating to the substrate; and further heating the substrate to melt the plugs. | 2020-01-23 |
20200025086 | CROSS-STREAM HEAT EXCHANGER - A heat exchanger system for a gas turbine engine is disclosed. The heat exchanger system may include a first structure at least partially defining a first plenum configured to receive a first air stream, a second structure at least partially defining a second plenum configured to receive a second air stream having lower pressure than the first air stream, a third structure at least partially defining a third plenum configured to receive a third air stream having lower pressure than the second air stream, and a heat exchanger configured for operative communication with the first air stream, the second air stream, and the third air stream while disposed between the second air stream and the third air stream. The heat exchanger may be configured to transfer heat from the first air stream to the third air stream. | 2020-01-23 |
20200025087 | CONNECTING GAS TURBINE ENGINE ANNULAR MEMBERS - A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively. | 2020-01-23 |
20200025088 | AIRCRAFT TURBOMACHINE ASSEMBLY COMPRISING AN ARTICULATED COWL - A turbomachine assembly for an aircraft comprising a nacelle with a nacelle structure, cowls attached to the structure to create an aerodynamic surface, an articulated cowl, comprising four edges, in the upper portion of the nacelle, an articulation at a first edge of the articulated cowl attached between the articulated cowl and the nacelle structure allowing the articulated cowl to move between a closed and an open position, a locking system at a second edge of the articulated cowl, opposite the first edge. The locking system comprises a handle actuable from the exterior of the nacelle, between a first position and a second position, a locking device movable between a locking position and an unlocking position, and a transmission system that moves the locking device from the locking position to the unlocking position when the handle passes from the first position to the second position, and vice versa. | 2020-01-23 |
20200025089 | GAS TURBINE COMBUSTOR - A combustor of an embodiment includes: a cylindrical combustor liner; and a fuel nozzle which is provided at one end of the combustor liner and jets a fuel and an oxidant into the combustor liner. The fuel nozzle includes: a plurality of fuel supply passages which each supply the fuel; and a plurality of oxidant supply passages which each supply the oxidant. Flow rates of the fuel supplied to the respective fuel supply passages and flow rates of the oxidant supplied to the respective oxidant supply passages are each individually regulated. | 2020-01-23 |
20200025090 | FUEL DISTRIBUTION WITHIN A GAS TURBINE ENGINE COMBUSTOR - A fuel system for a gas turbine engine includes a plurality of duplex nozzles arranged on each side of top dead center and a plurality of simplex nozzles. A primary manifold is operable to communicate fuel to a primary flow jet in each of the plurality of duplex nozzles and a secondary manifold is operable to communicate fuel to a secondary flow jet in each of the plurality of duplex nozzles and a secondary flow jet in each of the plurality of simplex nozzles. An equalizer valve that is in communication with both the primary manifold and the secondary manifold distributes fuel at various pressures to both the primary and secondary manifolds. | 2020-01-23 |
20200025091 | SELF-REGULATING BACK-SIDE PRESSURIZATION SYSTEM FOR THERMAL INSULATION BLANKETS - High-pressure fan duct bleed air is used to pressurize a cavity between the fan duct inner wall and the inner wall thermal insulation blankets. The cavity is pressurized to prevent hot air from the nacelle core compartment from flowing under the insulation blankets and degrading the fan duct inner wall. Pressure regulating valves (PRV) allow better control of the cavity pressure during different phases of the flight profile and under different levels of insulation blanket seal degradation by passively controlling exit area from the cavity based on an established pressure limit. Moreover, the pressurization system can be implemented as a passive cooling system by increasing the mass flow rate into the cavity and then the core compartment to a level suitable for core compartment cooling. The cooling air can be vented at the forward end of the insulation blanket assembly to provide core compartment ventilation flow, or vented through dedicated ports in the insulation blanket for targeted core compartment component cooling. | 2020-01-23 |
20200025092 | GAS TURBINE ENGINE AND PANEL FOR A GAS TURBINE ENGINE - A gas turbine engine for an aircraft includes: a flow path boundary, which delimits the flow path through the engine radially on the outside, and a lining, which lines the flow path boundary on the inside, at least along an axial section. Here, the lining includes a plurality of panels, which, in the circumferential direction of the flow path boundary, adjoin each other and which together line a circumferential area of 360°, wherein each panel has two end faces, which each adjoin an end face of an adjacent panel. The panels are of beveled design at their end faces, such that two mutually adjoining panels form a V-shaped gap between them, the minimum clearance of which is realized at the inside of the panels. The panels can be sound-absorbing panels. Also disclosed is a panel for a gas turbine engine. | 2020-01-23 |
20200025093 | GAS TURBINE ENGINE HEATSHIELD - A gas turbine engine for an aircraft is provided. The engine includes an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The engine further includes a core casings surrounding the engine core. The engine further includes one or more engine accessories mounted adjacent to and vertically beneath the core casings. The engine further includes a heatshield positioned between the one or more engine accessories and the core casings. The heatshield contains one or more ventilation holes for channelling convectively driven flows of ventilation air around the one or more engine accessories on engine shutdown. | 2020-01-23 |
20200025094 | METHOD FOR ALLOCATING POWER IN AN ELECTRICAL POWER SYSTEM ARCHITECTURE - An electrical power system architecture and method for allocating power includes a power distribution bus configured to receive power generated by a first engine having a first generator and a second generator, a first set of electrical buses connected with the power distribution bus and associated with the first engine, and a second set of electrical buses configured to selectively connect with the power distribution bus. | 2020-01-23 |
20200025095 | SELF-ERODING SINGLE-USE GAS-TURBINE-ENGINE IGNITER - A sacrificial outer sleeve of a self-eroding single-use gas-turbine-engine igniter contains a main pyrotechnic composition and an initiator embedded therein proximate to a distal portion of the sacrificial outer sleeve. The sacrificial outer sleeve extends within a combustion chamber of the gas-turbine engine when operatively coupled thereto so as to provide for igniting a fuel/air mixture therein. The sacrificial outer sleeve is constructed of a material that is consumable either responsive to combustion of the main pyrotechnic composition responsive to activation of the initiator responsive to an actuation signal communicated via an associated signal conduit, or, responsive to a subsequent operation of said gas-turbine engine to which the igniter is operatively coupled, when operatively coupled thereto. | 2020-01-23 |
20200025096 | Aeroderivative Jet Engine Accessory Starter Relocation to Main Shaft - Directly Connected to HPC Shaft - In one aspect, the present disclosure is directed to a gas turbine starting system that includes a shaft coupling a compressor and a turbine. An annular housing extends circumferentially around the shaft such that the annular housing defines a compartment. A flange extends radially outward from the annular housing for mounting the annular housing to a stationary wall. A starter is positioned in the compartment. A collar rotatably couples to the annular housing and selectively couples to the starter. The collar includes a radially inner surface having a plurality of splines for engaging the shaft. The starter, when activated, rotates the collar, which rotates the shaft to start the gas turbine. | 2020-01-23 |
20200025097 | HYDROSTATIC SEAL WITH ABRADABLE TEETH FOR GAS TURBINE ENGINE - A hydrostatic seal assembly includes a seal support, a seal shoe integral to the seal support and radially movable relative to the seal support. A plurality of seal teeth are located at a radially inboard surface of the seal shoe. The seal shoe is formed from a first material and the radially inboard surface is formed from a second material softer than the first material such that the radially inboard surface is abradable in the event of a rub between the radially inboard surface and an adjacent rotating component. | 2020-01-23 |
20200025098 | BOLTED DUCT JOINTS - A first duct segment may include a first flange including a first planar mating face and a first recess. A second duct segment may include a second flange including a second planar mating face and a second recess. The first duct segment and the second duct segment may be installed in a gas turbine engine. A first E-seal may be inserted in the first recess, and a second E-seal may be inserted in the second recess. A gap may be measured between the first flange and the second flange. A flat shim may be selected based on the size of the gap. The flat shim may be inserted between the first flange and the second flange. A plurality of bolts may be inserted through the first flange, the flat shim, and the second flange to seal the first duct segment to the second duct segment. | 2020-01-23 |
20200025099 | GAS TURBINE ENGINE - A gas turbine engine for an aircraft, comprising: an engine core; a covering configured to cover at least part of the engine core; and an engine accessory that interacts with the engine core or a component of the engine core; wherein the engine accessory is outside the covering. | 2020-01-23 |
20200025100 | ACCESSORY RELAY FOR GAS TURBINE ENGINE - Accessory relay ( | 2020-01-23 |
20200025101 | GEARED TURBOFAN WITH INTEGRAL FRONT SUPPORT AND CARRIER - A gas turbine engine includes a nacelle, and a bypass flow path in a bypass duct within the nacelle of the turbofan engine. A fan section includes a fan with fan blades. The fan section drives air along the bypass flow path. A fan shaft drives a fan that has fan blades and the fan rotates about a central longitudinal axis of the turbofan engine. A speed reduction device includes an epicyclic gear system. A turbine section is connected to the fan section through the speed reduction device and the turbine section rotates about the central longitudinal axis. A first fan bearing for supporting rotation of the fan hub is located axially forward of the speed reduction device. A second fan bearing for supporting rotation of the fan hub is located axially aft of the speed reduction device. A first outer race of the first fan bearing is fixed relative to the fan hub. | 2020-01-23 |
20200025102 | PLANETARY GEAR, SPLINED SLEEVE, GAS TURBINE ENGINE WITH A PLANETARY GEAR AND METHOD FOR MANUFACTURING A PLANETARY GEAR - A planetary gearbox, a splined sleeve, a gas turbine engine with a planetary gearbox and a method for producing a torque-proof connection between a planetary carrier and a support element. The splined sleeve is formed with an outer substantially cylindrical shell surface area and an inner conical shell surface area, and is inserted between the planetary carrier and the support element for creating the torque-proof connection. The diameter of the inner conical shell surface area decreases in the axial direction, starting from an end of the splined sleeve in the direction of a second end of the splined sleeve. The outer cylindrical shell surface area is formed in a stepped manner. The outer cylindrical shell surface area comprises a first cylindrical section and a second cylindrical section which has a diameter larger than the diameter of the first cylindrical section. Between the sections, a conical area is provided. | 2020-01-23 |
20200025103 | GEARING ARRANGEMENT AND METHOD FOR MANUFACTURING THE GEARING ARRANGEMENT - A gearbox assembly for a gas turbine engine comprises a planetary gearbox having at least one ring gear and at least one planet gear, which exerts a force on the ring gear in the direction of a force vector as it rolls on said ring gear; and a holding device for fastening the at least one ring gear on another structure, having a first section, which extends in the axial direction on one side of the force vector and/or of a straight-line extension thereof, and having a second section, which extends in the axial direction on the other side of the force vector and/or of the straight-line extension thereof. A gas turbine engine and a method for producing a gearbox assembly are furthermore made available. | 2020-01-23 |
20200025104 | MULTI-BYPASS STREAM GAS TURBINE ENGINE WITH ENLARGED BYPASS FLOW AREA - A gas turbine engine comprises a first bypass flow path housing configured within the engine, radially exterior to an engine core housing, and a second bypass flow path housing configured within the engine, radially exterior to the first bypass flow path housing. An axially downstream portion of the first bypass flow path housing includes a stepwise increase in area compared with an axially adjacent upstream portion of the first bypass flow path housing, thereby defining a component placement cavity in the axially downstream portion. | 2020-01-23 |
20200025105 | INTERCOOLED COOLING AIR WITH AUXILIARY COMPRESSOR CONTROL - A gas turbine engine includes a main compressor section with a downstream most location. A turbine section has a high pressure turbine. A tap line is connected to tap air from a location upstream of the downstream most location in the main compressor section. The tapped air is connected to a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and is connected to deliver air into the high pressure turbine. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions. | 2020-01-23 |