Patent application number | Description | Published |
20160032726 | GAS TURBINE ENGINE AXIAL COMPRESSOR REAR HUB - A gas turbine engine includes an axial high pressure compressor includes a rear hub disposed aft of an aft rotor segment. The rear hub includes an inner surface, an outer surface, and a sealing face, wherein the sealing face is sealingly engaged with the aft rotor segment, and in fluid communication with the cooling channel. The cooling channels are configured to delivery air to contact the inner surface of the rear hub. | 02-04-2016 |
20160032753 | GAS TURBINE ENGINE WITH AXIAL COMPRESSOR HAVING IMPROVED AIR SEALING - A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment. The fore end of the slots may have an axial seal which is coupled to the inner surface of the outer rim in the first rotor segment, and may comprise a fin configuration. The axial seal may be integral to the inner surface of the outer rim. The compressor may comprise a plurality of expansion slots and axial seals, including in a plurality of rotor segments. | 02-04-2016 |
20160032767 | GAS TURBINE ENGINE WITH AXIAL COMPRESSOR WITH INTERNAL COOLING PATHWAYS - A gas turbine engine may include an axial high pressure compressor having an air flow pathway positioned between the inner and outer rim of the rotor section. The air flow pathway includes an inlet port, a transition segment, an axial segment, and an outlet port. The pathway may be a tube having an ovoid cross sectional shape and is substantially co-planar to the outer surface of the outer rim. The pathway may traverse the rotor section from the first rotor segment to the rear hub. | 02-04-2016 |
20160032937 | GAS TURBINE ENGINE AXIAL DRUM-STYLE COMPRESSOR ROTOR ASSEMBLY - A gas turbine engine includes an axial compressor which includes a rotor assembly including a first rotor segment with a first inner rim, a first sealing surface, and a first aft engagement feature, and a second rotor segment positioned aft of the first rotor segment and having a second inner rim, a second sealing surface, and a second inner rim with a second fore engagement feature that is complementary to the first aft engagement feature. The first and second sealing surfaces are complementary to each other, and are bonded together via a transient liquid phase diffusion process. The first and second sealing surfaces are disposed on the outer rim. The first aft engagement member may be a notch that is complementary to the second fore engagement feature, which may be a shelf. | 02-04-2016 |
Patent application number | Description | Published |
20080310955 | Hybrid cooling of a gas turbine engine - A hybrid cooling system for a gas turbine engine includes a vapor cooling assembly and a cooling air cooling assembly. The cooling air cooling assembly is configured to remove thermal energy from cooling air used to cool a first component of the gas turbine engine. The vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly. The vaporization section is located at least partially within a second component of the gas turbine engine, and the condenser section is located outside the second component. | 12-18-2008 |
20090148282 | 3D CONTOURED VANE ENDWALL FOR VARIABLE AREA TURBINE VANE ARRANGEMENT - A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing. | 06-11-2009 |
20090293496 | GAS TURBINE ENGINES GENERATING ELECTRICITY BY COOLING COOLING AIR - A portion of cooling air for cooling the turbine section of a gas turbine engine is tapped and passed through a heat exchanger. The portion of the cooling air is cooled in the heat exchanger, and the heat taken out of the portion of the cooling air is utilized to generate electricity. | 12-03-2009 |
20100263388 | Vapor cooled static turbine hardware - A cooling system for a gas turbine engine includes a non-rotating component extending into an engine flowpath, a vapor cooling assembly configured to transport thermal energy from a vaporization section to a condenser section through cyclical evaporation and condensation of a working medium sealed within the vapor cooling assembly, wherein the vaporization section is located at least partially within the non-rotating component, and wherein the condenser section is located outside the non-rotating component and away from the engine flowpath. | 10-21-2010 |
20120006034 | HYBRID COOLING OF A GAS TURBINE ENGINE - A method for cooling components of a gas turbine engine, having first and second sets of components that require cooling, includes removing thermal energy from cooling air, directing the cooling air from which thermal energy has been removed to the first set of components of the gas turbine engine, and transferring thermal energy away from the second set of components of the gas turbine engine using a vaporization cycle of a vapor cooling assembly. Use of the vaporization cycle offsets thermal energy removed from the cooling air. | 01-12-2012 |
20120020805 | REVERSE CAVITY BLADE FOR A GAS TURBINE ENGINE - A rotor blade for a turbine engine includes an airfoil section which extends from a platform section opposite a root section, the airfoil section defines a cavity which extends from an airfoil tip section toward a root section. | 01-26-2012 |
20130142665 | HYBRID VAPOR AND FILM COOLED TURBINE BLADE - A cooling system for cooling a fluid reaction apparatus of a gas turbine engine includes a vapor cooling subsystem and a film cooling subsystem. The vapor cooling subsystem has a vaporization section and a condenser section for cooling a portion of the fluid reaction apparatus. The condenser section is cooled by a fluid. The film cooling subsystem is configured for cooling a portion of the fluid reaction apparatus by discharging fluid out of openings defined in the fluid reaction apparatus. At least a portion of the fluid used to cool the condenser section of the vapor cooling subsystem is discharged out of the openings of the film cooling subsystem. | 06-06-2013 |
20140311121 | PULSE DETONATION ENGINE HAVING A SCROLL EJECTOR ATTENUATOR - The engine ( | 10-23-2014 |
20150184860 | SPIRAL PULSE DETONATION TUBE CONFIGURATION - An engine includes an elongated pulse detonation combustor tube having an arcuate combustion path over a majority of an entire length of the combustor tube, and an elongated portion of the combustor tube being oriented transverse to a central axis of the engine. | 07-02-2015 |
20150247456 | OFFSET CORE ENGINE ARCHITECTURE - A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan. | 09-03-2015 |
20150285147 | Cooling System with a Bearing Compartment Bypass - A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section. | 10-08-2015 |
20150354389 | SEGMENTED RIM SEAL SPACER FOR A GAS TURBINE ENGINE - A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box. | 12-10-2015 |
20150354455 | THERMALLY ISOLATED TURBINE SECTION FOR A GAS TURBINE ENGINE - A gas turbine engine includes a turbine section fluidly connected to a combustor by a primary flow path. The turbine section includes a first portion at a high pressure relative to a second portion. A thermally isolated cooling plenum is positioned radially inward of the primary flow path. The cooling plenum is defined by a forward wall, a shaft structure, an aft wall, and an inner diameter wall of the primary flow path. Air in the thermally isolated cooling plenum is thermally isolated from air in the primary flow path. At least one cooling air system is operable to provide cooling air to the thermally isolated cooling plenum. | 12-10-2015 |
20150354456 | COOLING SYSTEM FOR GAS TURBINE ENGINES - A cooling system for gas turbine engines includes a turbine rotor compartment defining a cooling air plenum. A plurality of turbine discs are rotatably housed within the rotor compartment. A cooling air inlet is in fluid communication with the plenum. Each turbine disc includes a cooling outlet in fluid communication with the plenum for cooling the rotor compartment. | 12-10-2015 |
20150354465 | TURBINE STAGE COOLING - A turbine cooling air generation system for a gas turbine engine includes a first fluid pathway connecting a compressor bleed outlet and a mixing valve, a second fluid pathway connecting the compressor bleed outlet and an input of a heat exchanger, and a third fluid pathway connecting an output of the heat exchanger and the mixing valve. The mixing valve is further connected to an input of a turbine stage active cooling system. | 12-10-2015 |
20150354822 | TURBINE STAGE COOLING - A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system. | 12-10-2015 |
20150361890 | HIGH PRESSURE TURBINE COOLING - A gas turbine engine includes a compressor section having a plurality of compressor stages, a combustor fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, the turbine section having at least one stage, a compressor bleed structure disposed in one of the plurality of compressor stages and operable to remove air from the compressor stage, a heat exchanger having an input connected to the compressor bleed, and an output connected to an active cooling system of at least one turbine stage, and wherein the compressor stage in which the compressor bleed structure is disposed includes airflow at a pressure above a minimum pressure threshold, and wherein the airflow has a temperature above a maximum temperature threshold. | 12-17-2015 |
20150369130 | SYSTEMS AND METHODS FOR DISTRIBUTING COOLING AIR IN GAS TURBINE ENGINES - Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section. | 12-24-2015 |
20150377052 | SEGMENTED SEAL FOR A GAS TURBINE ENGINE - A seal segment according to an exemplary aspect of the present disclosure includes, among other things, a first axial wall, a second axial wall radially spaced from the first axial wall and a radially outer wall that interconnects the first axial wall and the second axial wall. At least one curved member is radially inwardly offset from the radially outer wall and extending between the first and second axial walls. | 12-31-2015 |
20160003058 | ROTOR AND GAS TURBINE ENGINE INCLUDING SAME - A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, adjacent ones of the plurality of blades are joined by a flexible web. | 01-07-2016 |
20160023307 | Process for Manufacturing a Gamma Titanium Aluminide Turbine Component - A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique. | 01-28-2016 |
20160024935 | GAS TURBINE ENGINE BLADE WITH VARIABLE DENSITY AND WIDE CHORD TIP - A blade for a gas turbine engine includes a body that includes an airfoil that extends in a radial direction from a 0% span position near an airfoil base to a 100% span position at an airfoil tip. The airfoil includes a first portion near the airfoil base with a first density and includes a second portion near the airfoil tip with a second density. The second density is less than the first density. The second portion includes an increasing true chord length in the radial direction. | 01-28-2016 |
20160025040 | GAS DYNAMIC VALVE - A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess. | 01-28-2016 |
20160032731 | THERMAL BARRIER COATING INSIDE COOLING CHANNELS - A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed. | 02-04-2016 |
Patent application number | Description | Published |
20110082342 | ORIFICE INTRODUCER DEVICE - An orifice introducer device for introducing, e.g., a surgical device, into, e.g., an orifice of a body, includes a tubular member having a distal end and a proximal end. The distal end is adjustable between a first position for insertion into an orifice and a second position once inserted into the orifice. Alternatively, the orifice introducer device includes a distal portion having a proximal end configured to be detachably secured to the distal end of the tubular member. The distal portion is selectively detachable when the orifice introducer device is positioned in the orifice. | 04-07-2011 |
20110144679 | TROCAR DEVICE - A surgical device is described. The surgical device may comprise a rotatable cutter configured to cut tissue for insertion of a cannula, and a first driver configured to be driven by a motor arrangement and to rotate the cutter. The surgical device may further include, for example, the cannula, at least one of the rotatable cutter and the first driver being disposed in a bore of the cannula. In one embodiment, the rotatable cutter may include an auger having a cutting thread. In another embodiment, the rotatable cutter may include a disk-shaped blade. | 06-16-2011 |
20110144681 | TROCAR DEVICE - A surgical device is described. The surgical device may comprise a rotatable cutter configured to cut tissue for insertion of a cannula, and a first driver configured to be driven by a motor arrangement and to rotate the cutter. The surgical device may further include, for example, the cannula, at least one of the rotatable cutter and the first driver being disposed in a bore of the cannula. In one embodiment, the rotatable cutter may include an auger having a cutting thread. In another embodiment, the rotatable cutter may include a disk-shaped blade. | 06-16-2011 |
20110166587 | TROCAR DEVICE - A surgical device is described. The surgical device may comprise a rotatable cutter configured to cut tissue for insertion of a cannula, and a first driver configured to be driven by a motor arrangement and to rotate the cutter. The surgical device may further include, for example, the cannula, at least one of the rotatable cutter and the first driver being disposed in a bore of the cannula. In one embodiment, the rotatable cutter may include an auger having a cutting thread. In another embodiment, the rotatable cutter may include a disk-shaped blade. | 07-07-2011 |
Patent application number | Description | Published |
20090238438 | METHOD AND APPARATUS FOR DETERMINING RED BLOOD CELL INDICES OF A BLOOD SAMPLE UTILIZING THE INTRINSIC PIGMENTATION OF HEMOGLOBIN CONTAINED WITHIN THE RED BLOOD CELLS - A method for the determination of the red blood cell indices including the volume, and hemoglobin content and concentration for individual red blood cells, as well as red blood cell population statistics, including total number of red blood cells present in the sample, and mean values for each of the aforementioned indices within a substantially undiluted blood sample is provided. | 09-24-2009 |
20110059481 | METHOD AND APPARATUS FOR DETERMINING RED BLOOD CELL INDICES OF A BLOOD SAMPLE UTILIZING THE INTRINSIC PIGMENTATION OF HEMOGLOBIN CONTAINED WITHIN THE RED BLOOD CELLS - A method for the determination of the red blood cell indices including the volume, and hemoglobin content and concentration for individual red blood cells, as well as red blood cell population statistics, including total number of red blood cells present in the sample, and mean values for each of the aforementioned indices within a substantially undiluted blood sample is provided. | 03-10-2011 |
20110149061 | METHOD AND APPARATUS FOR IDENTIFYING RETICULOCYTES WITHIN A BLOOD SAMPLE - A method and apparatus for identifying reticulocytes within a blood sample is provided. The method includes the steps of: a) depositing the sample into an analysis chamber adapted to quiescently hold the sample for analysis, and the chamber has a known or determinable height extending between the interior surfaces of panels, which height is such that at least one red blood cell, or an aggregate of red blood cells, within the sample contacts both of the interior surfaces; b) admixing a supravital dye with the sample, which dye is operable to cause reticulin to fluoresce when excited by light of one or more predetermined wavelengths; c) imaging the sample using light that includes the one or more predetermined wavelengths that cause reticulin to fluoresce; d) imaging the sample using light that is absorbed by hemoglobin to produce values of optical density on a per image unit basis; and e) identifying reticulocytes within the sample using the image of the sample created with light that causes the dyed reticulin to fluoresce, and using the per image unit optical density values. | 06-23-2011 |
20130170729 | METHOD AND APPARATUS FOR IDENTIFYING RETICULOCYTES WITHIN A BLOOD SAMPLE - A method and apparatus for identifying reticulocytes within a blood sample is provided. The method includes the steps of: a) depositing the sample into an analysis chamber adapted to quiescently hold the sample for analysis, and the chamber has a known or determinable height extending between the interior surfaces of panels, which height is such that at least one red blood cell, or an aggregate of red blood cells, within the sample contacts both of the interior surfaces; b) admixing a supravital dye with the sample, which dye is operable to cause reticulin to fluoresce when excited by light of one or more predetermined wavelengths; c) imaging the sample using light that includes the one or more predetermined wavelengths that cause reticulin to fluoresce; d) imaging the sample using light that is absorbed by hemoglobin to produce values of optical density on a per image unit basis; and e) identifying reticulocytes within the sample using the image of the sample created with light that causes the dyed reticulin to fluoresce, and using the per image unit optical density values. | 07-04-2013 |