SIDE-FED SHIELDED INTERNAL FUEL MANIFOLD INLET TUBE

An inlet tube for supplying fuel to a fuel manifold in a gas turbine engine is disclosed. The fuel manifold lies in a plane substantially perpendicular to a central axis of the fuel manifold. The inlet tube includes a tube body defining a central axis extending between an inlet of the tube body and an outlet of the tube body, and at least a first and a second fuel channel defined through the tube body between the inlet and the outlet, The first and second fuel channels are located side by side within the tube body, and outlets of the first and second fuel channels are in fluid communication with the manifold. At least a portion of the tube body is offset from the plane of the fuel manifold.

ANNULAR GAS TURBINE ENGINE CASE AND METHOD OF MANUFACTURING

The method comprises flowforming at least one section of the preform and then welding at least one additional element to the at least one flowformed section.

TURBINE WASH PORT FOR A GAS TURBINE ENGINE

An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.

SIDE-FED SHIELDED INTERNAL FUEL MANIFOLD INLET TUBE

An inlet tube for supplying fuel to a fuel manifold in a gas turbine engine is disclosed. The fuel manifold lies in a plane substantially perpendicular to a central axis of the fuel manifold. The inlet tube includes a tube body defining a central axis extending between an inlet of the tube body and an outlet of the tube body, and at least a first and a second fuel channel defined through the tube body between the inlet and the outlet, The first and second fuel channels are located side by side within the tube body, and outlets of the first and second fuel channels are in fluid communication with the manifold. At least a portion of the tube body is offset from the plane of the fuel manifold.

Integral heater for fuel conveying member

A fuel conveying member for an engine, the fuel conveying member having heating means integrated therein to permit pyrolysis of carbonaceous deposits.

PRE-LOADED INTERNAL FUEL MANIFOLD SUPPORT

A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or the gas generator case. A biasing member is located between the fastener pin and the receiving element to axially preload the joint between the fastener pin and the receiving element, such as to constrain relative movement between the two parts in an axial direction while allowing relative movement in a radial direction.

PRE-LOADED INTERNAL FUEL MANIFOLD SUPPORT

A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or the gas generator case. A biasing member is located between the fastener pin and the receiving element to axially preload the joint between the fastener pin and the receiving element, such as to constrain relative movement between the two parts in an axial direction while allowing relative movement in a radial direction.

INTERNAL FUEL MANIFOLD WITH TURNED CHANNEL HAVING A VARIABLE CROSS-SECTIONAL AREA

A method of manufacturing an internal manifold of a gas turbine engine (10) including machining an annular channel (36) in a ring (22) by a turning process, and varying a position of a tool bit (80) relative to the surface (38) of the ring as a function of a relative circumferential location of the tool bit (80) around the ring (22) such that the channel (36) has a cross-sectional area that varies around a circumference of the ring.

REDUNDANT MOUNTING SYSTEM FOR AN INTERNAL FUEL MANIFOLD

A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

Testing rig and method for a fuel nozzle assembly

A method for testing a fuel nozzle assembly including blocking all but a selected number of the fuel nozzles with a flow impeding assembly and moving part of a rig to align the selected number of the fuel nozzles with at least one flow measurement apparatus.

Fuel conveying member with side-brazed sealing members

A gas turbine engine fuel nozzle system having a fuel conveying member with a channel formed in a surface thereof defined between a pair of facing spaced apart walls, and at least one sealing member disposed within the channel and sealingly fastened to the spaced apart walls.

INTERNAL FUEL MANIFOLD WITH TURNED CHANNEL HAVING A VARIABLECROSS-SECTIONAL AREA

REDUNDANT MOUNTING SYSTEM FOR AN INTERNAL FUEL MANIFOLD

A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

AIR COOLER FOR GAS TURBINE ENGINE

A turbofan engine comprising an outer bypass duct, an annular bypass flow path between the outer bypass duct and a core engine, an engine component forming an airflow obstruction adjacent the outer bypass duct, an air cooler having a tube, the tube having at least a sinuous portion extending in the annular bypass flow path, the sinuous portion extending along the outer bypass duct, downstream of the airflow obstruction, the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine.

GAS TURBINE ENGINE WITH TRAILING EDGE HEAT EXCHANGER

A gas turbine engine includes a fan assembly, a compressor assembly, a combustion chamber, a turbine assembly, a bypass duct conveying rearward a bypass airstream driven by the fan assembly when the gas turbine engine is in use, a fairing extending across at least a portion of the bypass duct downstream of the fan assembly, and a heat exchanger having an inlet fluidly connected to the compressor assembly and an outlet fluidly connected to a pneumatic actuator of the gas turbine engine. The fairing has a leading edge and a trailing edge. The heat exchanger is disposed adjacent the trailing edge of the fairing.

TURBINE WASH PORT FOR A GAS TURBINE ENGINE

Internal fuel manifold with turned channel having a variable cross-sectional area

A method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool bit around the ring such that the channel has a cross-sectional area that varies around a circumference of the ring.

Gas turbine internal manifold mounting arrangement

A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing.

Optimized internal manifold heat shield attachment

A fuel manifold assembly for a gas turbine engine includes an annular fuel manifold having at least one fuel conveying passage and defining at least one slow fuel flowing location. A heat shield at least partly encloses the fuel manifold and a plurality of intermittent joints attach the heat shield to the fuel manifold. The joints are circumferentially distributed about the fuel manifold as far away from the slow flowing location as possible while maintaining the fuel manifold dynamically balanced.

Gas turbine internal manifold mounting arrangement

A mounting system for an annular internal fuel manifold of a gas turbine engine includes three supports equally spaced apart about the annular fuel manifold, the three supports having at least two pin supports disposed between the fuel manifold and a surrounding gas generator casing. Each pin support includes a radially extending pin co-operating with an aligned ring slidingly disposed around the pin for relative sliding displacement therebetween. The pin supports providing axial constraint while permitting the fuel manifold to radially displace relative to the surrounding gas generator casing due to thermal size change.

OPTIMIZED INTERNAL MANIFOLD HEAT SHIELD ATTACHMENT

A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold having at least one fuel conveying passage and defining at least one slow fuel flowing location. A heat shield at least partly encloses the fuel manifold and a plurality of intermittent joints attach the heat shield to the fuel manifold. The joints are circumferentially distributed about the fuel manifold as far away from the slow flowing location as possible while maintaining the fuel manifold dynamically balanced.

Turbine wash port for a gas turbine engine

An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.

Fuel manifold inlet tube

An inlet tube supplies fuel to a manifold of a combustor in a gas turbine engine, the manifold defining a manifold plane. The inlet tube comprises a tube body having a channel providing fluid flow communication between first and second ends of the tube body. At least a portion of the channel defines a tube body plane which is spaced apart from the manifold plane.

GAS TURBINE INTERNAL MANIFOLD MOUNTING ARRANGEMENT

A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing. 1. A method for mounting an annular internal fuel manifold relative to a combustor within a gas generator casing of a gas turbine engine , the method comprising:positioning the fuel manifold within a gas generator casing;applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, the heat shield extending along a length of the fuel inlet disposed between the fuel manifold and the gas generator casing; andusing the heat shield to at least partially support the fuel manifold within the gas generator casing by mounting the heat shield such that a proximal end thereof is in direct load bearing engagement with one or both of the fuel inlet and the gas generator casing and a distal end in direct load bearing engagement with the fuel manifold, such that the heat shield provides a load path therethrough which significantly reduces the load born by the fuel inlet, the heat shield thereby bear more load than the fuel inlet to support the fuel manifold.2. The method as defined in claim 1 , further comprising supporting the fuel manifold within the gas generator casing using at least three supports equally spaced about the annular fuel manifold claim 1 , one of said three supports including the heat shield.3. The method as defined in claim 1 , wherein the step of applying the heat shield further comprises mounting the heat shield between the fuel manifold and the gas generator casing claim 1 , the heat shield covering at least a portion of the fuel inlet extending therebetween.4. The method as defined in ...

Fuel manifold inlet tube

In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, the side inlet being sealingly isolated by at least two annular sealing members concentric with each other and disposed about the tube body at longitudinally spaced part points thereon.

Gas turbine engine fuel conveying member

A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.

AIR COOLER FOR GAS TURBINE ENGINE

A turbofan engine comprising an outer bypass duct, an annular bypass flow path between the outer bypass duct and a core engine, an engine component forming an airflow obstruction adjacent the outer bypass duct, an air cooler having a tube, the tube having at least a sinuous portion extending in the annular bypass flow path, the sinuous portion extending along the outer bypass duct, downstream of the airflow obstruction, the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine. 1. A turbofan engine comprising an outer bypass duct , an annular bypass flow path between the outer bypass duct and a core engine , an engine component forming an airflow obstruction adjacent the outer bypass duct , an air cooler having a tube , the tube having at least a sinuous portion extending in the annular bypass flow path , the sinuous portion extending along the outer bypass duct , downstream of the airflow obstruction , the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine , wherein the sinuous portion has a circumferential span of at least 2% of a circumference of the annular bypass flow path.2. The turbofan engine of wherein the sinuous portion is positioned relative to the engine component in a manner to be shielded from foreign object damage by the engine component.3. The turbofan engine of wherein the sinuous portion has a sequence of straight portions oriented in opposite radial orientations and connected to one another by elbows.4. The turbofan engine of wherein the elbows are configured to generate mixing of the fluid circulating in the tube across a cross-section of the tube.5. The turbofan engine of wherein the sinuous portion has sinuous shape in a transversal plane.6. The turbofan engine of wherein the sinuous portion is radially ...

Gas turbine internal manifold mounting arrangement

A mounting system supporting and positioning an internal fuel manifold of a gas turbine engine includes at least a heat shield surrounding a fuel inlet of the fuel manifold, the heat shield bearing at least a portion of a load to support the fuel manifold.

GAS TURBINE INTERNAL MANIFOLD MOUNTING ARRANGEMENT

A mounting system supporting and positioning an internal fuel manifold of a gas turbine engine includes at least a heat shield surrounding a fuel inlet of the fuel manifold, the heat shield bearing at least a portion of a load to support the fuel manifold.

FUEL MANIFOLD INLET TUBE

In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, the side inlet being sealingly isolated by at least two annular sealing members concentric with each other and disposed about the tube body at longitudinally spaced part points thereon.

GAS TURBINE ENGINE FUEL CONVEYING MEMBER

A fuel conveying member for a gas turbine engine, the fuel conveying member including a fuel manifold having a plurality of fuel nozzles extending therefrom. The fuel manifold is mounted within the engine by a support system, including integral attachment lugs on the fuel manifold for mounting the fuel manifold within the gas turbine engine. The attachment lugs re adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.

GAS TURBINE ENGINE WITH TRAILING EDGE HEAT EXCHANGER

A gas turbine engine includes a fan assembly, a compressor assembly, a combustion chamber, a turbine assembly, a bypass duct conveying rearward a bypass airstream driven by the fan assembly when the gas turbine engine is in use, a fairing extending across at least a portion of the bypass duct downstream of the fan assembly, and a heat exchanger having an inlet fluidly connected to the compressor assembly and an outlet fluidly connected to a pneumatic actuator of the gas turbine engine. The fairing has a leading edge and a trailing edge. The heat exchanger is disposed adjacent the trailing edge of the fairing. 1. A gas turbine engine , comprisinga fan assembly, a compressor assembly, a combustion chamber, a turbine assembly, a bypass duct conveying rearward a bypass airstream driven by the fan assembly when the gas turbine engine is in use, and a fairing extending across at least a portion of the bypass duct downstream of the fan assembly, the fairing having a leading edge and a trailing edge, anda heat exchanger having an inlet fluidly connected to the compressor assembly and an outlet fluidly connected to a pneumatic actuator of the gas turbine engine, the heat exchanger being disposed adjacent to the trailing edge of the fairing.2. The gas turbine engine of claim 1 , wherein the heat exchanger is connected to the fairing via a bracket.3. The gas turbine engine of claim 2 , wherein the bracket is disposed at least in part inside the fairing.4. The gas turbine engine of claim 3 , wherein the bracket is disposed in its entirety inside the fairing and is attached to at least one inner surface of the fairing claim 3 , and the heat exchanger includes a body that completes a shape of the fairing claim 3 , and a tortuous fluid conduit disposed inside the body claim 3 , the inlet of the heat exchanger being one end of the tortuous fluid conduit and the outlet of the heat exchanger being at another end of the tortuous fluid conduit.5. The gas turbine engine of claim 1 , ...

Redundant mounting system for an internal fuel manifold

A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

Pre-loaded internal fuel manifold support

A system for mounting an internal fuel manifold within a gas generator case of a gas turbine engine includes at least one fastener support assembly having a fastener pin and at least one receiving element, respectively engaged to either the internal fuel manifold or the gas generator case. A biasing member is located between the fastener pin and the receiving element to axially preload the joint between the fastener pin and the receiving element, such as to constrain relative movement between the two parts in an axial direction while allowing relative movement in a radial direction.

HEAT SHIELD WITH STRESS RELIEVING FEATURE

A heat shield for a fuel member of a gas turbine engine having at least one heat shield segment having a connection edge with at least one joint receiving portion defined therealong for receiving a welded joint attaching the heat shield segment to a fuel member, each joint receiving portion including a stress relieving feature defined along at least one end thereof.

Fuel conveying member with side-brazed sealing members

A gas turbine engine fuel nozzle system having a fuel conveying member with a channel formed in a surface thereof defined between a pair of facing spaced apart walls, and at least one sealing member disposed within the channel and sealingly fastened to the spaced apart walls.

FUEL MANIFOLD INLET TUBE

An inlet tube supplies fuel to a manifold of a combustor in a gas turbine engine, the manifold defining a manifold plane. The inlet tube comprises a tube body having a channel providing fluid flow communication between first and second ends of the tube body. At least a portion of the channel defines a tube body plane which is spaced apart from the manifold plane.

Reduced stress internal manifold heat shield attachment

A fuel manifold assembly for a gas turbine engine fuel system comprises a fuel manifold at least partly enclosed by a heat shield, the internal manifold being made of a first material having a first coefficient of thermal expansion, and the heat shield being made of a second material having a second coefficient of thermal expansion that is lower than the first coefficient of thermal expansion.

REDUCED STRESS INTERNAL MANIFOLD HEAT SHIELD ATTACHMENT

A fuel manifold assembly for a gas turbine engine fuel system comprises a fuel manifold at least partly enclosed by a heat shield, the internal manifold being made of a first material having a first coefficient of thermal expansion, and the heat shield being made of a second material having a second coefficient of thermal expansion that is lower than the first coefficient of thermal expansion.

TURBINE WASH PORT FOR A GAS TURBINE ENGINE

An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.

Gas turbine internal manifold mounting arrangement

A mounting system for an annular internal fuel manifold of a gas turbine engine includes three supports equally spaced apart about the annular fuel manifold, the three supports having at least two pin supports disposed between the fuel manifold and a surrounding gas generator casing. Each pin support includes a radially extending pin co-operating with an aligned ring slidingly disposed around the pin for relative sliding displacement therebetween. The pin supports providing axial constraint while permitting the fuel manifold to radially displace relative to the surrounding gas generator casing due to thermal size change.

Internal fuel manifold with turned channel having a variable cross-sectional area

A method of manufacturing an internal manifold of a gas turbine engine including machining an annular channel in a ring by a turning process, and varying a position of a tool bit relative to the surface of the ring as a function of a relative circumferential location of the tool bit around the ring such that the channel has a cross-sectional area that varies around a circumference of the ring.

Heat shield with stress relieving feature

A heat shield for a fuel member of a gas turbine engine having at least one heat shield segment having a connection edge with at least one joint receiving portion defined therealong for receiving a welded joint attaching the heat shield segment to a fuel member, each joint receiving portion including a stress relieving feature defined along at least one end thereof.

METHODS AND COMPOSITIONS FOR MODULATING ANGIOGENESIS

The present invention provides compositions comprising antisense nucleic acids that reduce miR-126 levels in an endothelial cell. The present invention provides compositions comprising a target protector nucleic acid. The present invention provides methods of modulating angiogenesis in an individual, the methods generally involving administering to the individual an effective amount of an agent that increases or that decreases the level of miR-126 in endothelial cells of the individual. 117.-. (canceled)18. A method of reducing angiogenesis in a mammal , the method comprising administering to a mammal in need thereof an effective amount of an agent that decreases a level and/or activity of miR-126 in an endothelial cell in the mammal.19. The method of claim 18 , wherein the agent is: i) an antisense nucleic acid that reduces a level of miR-126 in the cell; ii) a nucleic acid comprising a nucleotide sequence encoding an antisense nucleic acid that reduces a level of miR-126 in the cell; iii) a nucleic acid comprising a nucleotide sequence that is complementary to a mature miR-126 nucleic acid and that inhibits binding of a mature miR-126 to a miR-126 target; or iv) a nucleic acid comprising a nucleotide sequence encoding a nucleic acid comprising a nucleotide sequence that is complementary to a mature miR-126 nucleic acid and that inhibits binding of a mature miR-126 to a miR-126 target.20. The method of claim 19 , wherein the antisense-encoding nucleotide sequence is operably linked to an endothelial-specific transcriptional control element.21. The method of claim 19 , wherein the antisense-encoding nucleotide sequence is operably linked to an inducible promoter.22. The method of claim 18 , wherein the agent is an antisense nucleic acid that reduces a level of miR-126 in the cell.23. The method of claim 22 , wherein the antisense nucleic acid forms a stable duplex with a portion of the miR-126 nucleic acid comprising a ribonuclease III cleavage site.24. The method ...

Bearing chamber pressurization system

A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing.

Internally mounted fuel manifold with support pins

A method and apparatus for internally mounting a fuel manifold within a surrounding casing in a gas turbine engine which involves inserting the fuel manifold into the casing with support elements positioned in a retracted position, displacing the support elements into an extended position, and fastening said support elements to mount the manifold to an inner surface of said casing.

Annular gas turbine engine case and method of manufacturing

The method comprises flowforming at least one section of the preform and then welding at least one additional case element to the at least one flowformed section, to form the additional case element having a first end and a second end, the first end of the additional case element having a diameter configured for connection with the second end of the flowformed annular case element and the second end of the additional case element having a diameter smaller than said diameter of the second end of the flowformed annular case element.

Heat shield with stress relieving feature

A heat shield for a fuel member of a gas turbine engine having at least one heat shield segment having a connection edge with at least one joint receiving portion defined therealong for receiving a welded joint attaching the heat shield segment to a fuel member, each joint receiving portion including a stress relieving feature defined along at least one end thereof.

Testing rig and method for a fuel nozzle assembly

A method for testing a fuel nozzle assembly including blocking all but a selected number of the fuel nozzles with a flow impeding assembly and moving part of a rig to align the selected number of the fuel nozzles with at least one flow measurement apparatus.

Internally mounted fuel manifold with support pins

A method and apparatus for internally mounting a fuel manifold (22) within a surrounding casing (26) in a gas turbine engine (10) which involves inserting the fuel manifold (22) into the casing (26) with support elements (30) positioned in a retracted position (34), displacing the support elements (30) into an extended position, and fastening said support elements (30) to mount the manifold to an inner surface (38) of said casing.

Integral heater for fuel conveying member

A fuel conveying member (22), such as a fuel manifold and/or fuel nozzles for a gas turbine engine (10), the fuel conveying member (22) having heating means (50) integrated therein to permit pyrolysis of carbonaceous deposits. The heating means preferably comprises an electrical resistance heating element (52) that burns off any coke within the fuel conveying member thereby performing in situ cleaning, or decoking, of the engine. An associated method of cleaning a fuel conveying member that includes removal of the pyrolyzed deposits is also disclosed.

Methods and compositions for modulating angiogenesis

The present invention provides compositions comprising antisense nucleic acids that reduce miR-126 levels in an endothelial cell. The present invention provides compositions comprising a target protector nucleic acid. The present invention provides methods of modulating angiogenesis in an individual, the methods generally involving administering to the individual an effective amount of an agent that increases or that decreases the level of miR-126 in endothelial cells of the individual.

Internally mounted fuel distributor with retaining bolts

Rotor balancing device and method

A gas turbine rotor assembly includes a shaft 20, an oil scoop 50 and a seal runner 56 coaxially attached to the shaft. The oil scoop has a first, integral counterbalance weight 80 and the seal runner has a second, integral counterbalance weight 82. The angular positions of the oil scoop 50 and the seal runner 56 on the shaft 20 are selected such that a shaft imbalance is compensated for by the counterbalance weight 80, 82. Similarly, any pair of annular components located on the rotor shaft can be machined to contain counterbalance weights similar to the preferred embodiment. A corresponding method of balancing an imbalanced shaft is also taught.

Low cost diffuser assembly for gas turbine engine

A gas turbine diffuser assembly and a method for assembling same, includes providing a loose fit between the diffuser body and the diffuser pipes. Damper members provide a snug attachment.

Improved bearing chamber pressurization system

A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing.

Redundant mounting system for an internal fuel manifold

A mounting system for an annular internal fuel manifold disposed within a gas generator case of a gas turbine engine including at least one fastener support assembly and at least one receiving element, each fastener support assembly including a primary fastener engaging the receiving element to constrain a relative movement between the fuel manifold and the gas generator case in an axial direction while allowing the relative movement in a radial direction and a secondary fastener in position to passively and automatically engage the receiving element upon failure of the primary fastener.

Combustor liner v-band louver

A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Circulating cardiovascular biomarkers and vascular stabilizing therapy

Recent literature on SARS-CoV-2 pathogenesis has suggested that the induction of substantial acute respiratory distress phenotypes is driven by a mismatched inflammatory response together with broad vascular dysfunction. While several detailed reports implementing multi-omic approaches have provided insight into the immune cell phenotypes involved in these processes, risk stratifying markers specific to COVID-19 and the vasculature have not been explored. Provided herein is a comprehensive, multi-omics-based description of the molecular antecedents to COVID-19 mortality, yielding new insights pertaining to the vasculature while highlighting the urgent need for clinical translation of novel biomarkers for disease prognosis.

Circulating cardiovascular biomarkers and vascular stabilizing therapy

Recent literature on SARS-CoV-2 pathogenesis has suggested that the induction of substantial acute respiratory distress phenotypes is driven by a mismatched inflammatory response together with broad vascular dysfunction. While several detailed reports implementing multi-omic approaches have provided insight into the immune cell phenotypes involved in these processes, risk stratifying markers specific to COVID-19 and the vasculature have not been explored. Provided herein is a comprehensive, multi-omics-based description of the molecular antecedents to COVID-19 mortality, yielding new insights pertaining to the vasculature while highlighting the urgent need for clinical translation of novel biomarkers for disease prognosis.

V-band-lüftungsschlitz für eine brennkammerwand