Class / Patent application number | Description | Number of patent applications / Date published |
060799000 | Having expansible connection | 25 |
20110079020 | AIR METERING DEVICE FOR GAS TURBINE ENGINE - An air metering apparatus for a secondary air system of gas turbine engine includes a metering gap defined between surfaces comprised of one or more metals having one of similar coefficients of thermal expansion or similar thermal expansions at an operating temperature. Provided is an air metering gap which undergoes thermal growth in a way which provides a suitable air metering gap during engine running conditions. | 04-07-2011 |
20120131929 | FLEXIBLE SEAL FOR GAS TURBINE ENGINE SYSTEM - A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections, and a reinforcement member positioned between two of the plurality of corrugate sections. | 05-31-2012 |
20130247585 | NON-COMBUSTION ENERGY SOURCE AND CONFIGURATION FOR BRAYTON CYCLE HEAT ENGINES - A Brayton cycle heat engine includes a compressor, a combustion chamber, and a turbine. The Brayton cycle heat engine also includes a heat exchanger positioned at least partially within the combustion chamber. The heat exchanger is configured to deliver thermal energy to the combustion chamber from an external source, heating air entering the combustion chamber from the compressor, where the air exits the combustion chamber and drives the turbine. | 09-26-2013 |
20140033735 | TURBOMACHINE INCLUDING HORIZONTAL JOINT HEATING AND METHOD OF CONTROLLING TIP CLEARANCE IN A GAS TURBOMACHINE - A gas turbomachine includes a casing having a first casing half including first and second edge portions and a second casing half including first and second edge sections. The first edge portion is configured and disposed to be joined to the first edge section to form a first horizontal joint and the second edge portion is configured and disposed to be joined to the second edge section to form a second horizontal joint. At least one of the first edge portion and the first edge section including a first fluid passage, and at least one of the second edge portion and second edge section including a second fluid passage. The first and second fluid passages are configured and disposed to guide heated fluid along respective ones of the first and second horizontal joints. | 02-06-2014 |
20140311162 | CONNECTION STRUCTURE OF EXHAUST CHAMBER, SUPPORT STRUCTURE OF TURBINE, AND GAS TURBINE - In a gas turbine, an exhaust casing and an exhaust chamber are connected by an exhaust chamber support that can absorb thermal expansion, and the exhaust chamber and an exhaust duct are connected by an exhaust duct support that can absorb thermal expansion. An insulator is mounted on an outer peripheral surface of the exhaust chamber, and the exhaust chamber support and the exhaust duct support are disposed outside the insulator in the form of a plurality of strips. Because the thermal stress at a connection portion of the exhaust chamber is reduced, the durability is enhanced. | 10-23-2014 |
20140352323 | FLEXIBLE BELLOWS IGNITER SEAL - A flexible bellows assembly is disclosed for sealing an engine igniter for use with an engine. The bellows assembly includes a mounting arrangement that is operable to be secured to a combustor diffuser instead of the combustor liner. The bellows has a component that impinges upon a surface of the combustor liner so as to form a sealed chamber between a metal diffuser and a ceramic combustion liner. An igniter passes through the sealed chamber and provides ignition to the combustor. | 12-04-2014 |
20150101345 | SEAL ASSEMBLY FOR A GAP BETWEEN OUTLET PORTIONS OF ADJACENT TRANSITION DUCTS IN A GAS TURBINE ENGINE - A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position. While in the first position, the second seal member is circumferentially spaced from the outlet portion of the second transition duct. While in the second position, the second seal member extends across the leakage gap and creates a seal with the outlet portion of the second transition duct to substantially prevent leakage through the leakage gap. | 04-16-2015 |
20150300253 | Reduced Length Transition Ducts - A transition duct defining an airflow pathway between a low pressure compressor and a high pressure compressor of a gas turbine engine is disclosed. The transition duct may comprise an inner wall and an outer wall located radially outward of the inner wall with respect to a central axis of the gas turbine engine. It may further comprise a first bend configured to turn the airflow radially inward with respect to the central axis, and a turning vane located at the first bend between the inner wall and the outer wall. The turning vane may be configured to assist the first bend in turning the airflow radially inward. | 10-22-2015 |
060800000 | Combustor or fuel system | 17 |
20080236170 | Transition-to turbine seal apparatus and transition-to-turbine seal junction of a gas turbine engine - One embodiment of a transition-to-turbine seal ( | 10-02-2008 |
20080276622 | FUEL NOZZLE AND METHOD OF FABRICATING THE SAME - A fuel nozzle includes a swirler assembly including a radially inner surface and a radially outer surface, a plurality of vanes coupled to the swirler assembly radially outer surface. Each vane includes a first sidewall and a second sidewall, the first and second sidewalls are joined at a leading edge and at an axially-spaced trailing edge, and a plurality of openings are formed through each respective vane. Each opening extends from the leading edge to the passage to define a flow passage that extends from the passage to the leading edge. A method for fabricating a fuel nozzle assembly is also described. | 11-13-2008 |
20090188258 | ALTERING A NATURAL FREQUENCY OF A GAS TURBINE TRANSITION DUCT - A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies. | 07-30-2009 |
20090241553 | Replaceable orifice for combustion tuning and related method - A combustor assembly having a transition piece and at least one orifice assembly in the transition piece, the orifice assembly comprising: a boss having an outside periphery and an inside periphery, the inside periphery including an annular seat and an upstanding flange formed with an annular, inwardly facing retaining ring groove, the boss fixed within an opening in the transition piece; an orifice plate having a bottom surface that is adapted to be received on the annular seat; and a retaining ring located in the retaining ring groove and at least partially engaged with the orifice plate. | 10-01-2009 |
20090288422 | Component arrangement, combustion chamber arrangement and gas turbine - A component arrangement is provided which includes two component elements with portions pushed one into the other, leaving a gap and arranged statically with respect to one another. The component arrangement also includes a sealing element sealing off the gap. One of the component elements has a groove which runs in the region of the gap to be sealed off and is open towards the other component element. The component that has the groove has a side face. The sealing element includes a holding element with a first side face and with a second side face and is arranged at least partially in the groove. The first side face of the holding element can be pushed against the side face of the groove by a pressure difference. The side face of the groove and/or the first side face of the holding element include/includes at least one pressure relief depression. | 11-26-2009 |
20100115966 | GAS TURBINE COMBUSTOR - In a gas turbine combustor, a cavity ( | 05-13-2010 |
20100300116 | Expansion Hula Seals - The present invention provides a hula seal for use with a combustor. The hula seal includes a number of legs that define a number of slots. The slots may include a number of expansion slots. | 12-02-2010 |
20110072830 | COMBUSTOR INTERFACE SEALING ARRANGEMENT - A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring arrangement is configured to seal with the turbine nozzle to control fluid flow from the combustion area and reduce leakage. | 03-31-2011 |
20110120144 | ANNULAR COMBUSTION CHAMBER FOR A TURBOMACHINE - An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution an annular flange for fastening to a casing of the turbomachine, the downstream end of the other wall of revolution of the chamber including a bearing mechanism which are spaced apart from another casing of the turbomachine when cold and bear radially on this casing when hot. | 05-26-2011 |
20130042631 | SEAL END ATTACHMENT - A seal end attachment is provided and includes a vessel through which a working fluid flows, the vessel being formed to define a recess with a mating surface therein, a seal contacting the mating surface and a pressing member being more responsive to a high temperature condition associated with the flow of the working fluid than the vessel and being disposed within the recess to press the seal against the mating surface responsive to the condition being present. | 02-21-2013 |
20130283817 | FLEXIBLE SEAL FOR TRANSITION DUCT IN TURBINE SYSTEM - A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a flexible seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct. The flexible seal includes a sheet having a first surface, an opposing second surface, and a peripheral edge therebetween. | 10-31-2013 |
20130283818 | CONVOLUTION SEAL FOR TRANSITION DUCT IN TURBINE SYSTEM - A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a convolution seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct. | 10-31-2013 |
20140123678 | ADJUSTABLE HANGER AND METHOD FOR GAS TURBINE ENGINE EXHAUST LINER - A hanger assembly includes a hanger having a threaded bore, a bushing attaching to an outer duct, a rotator cooperating with the hanger so that the hanger may rotate relative to an inner duct, and wherein the bushing engages the hanger during assembly. | 05-08-2014 |
20150052910 | APPARATUS AND METHOD FOR SERVICING GAS TURBINE ENGINES - The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure. A drive member may be accessible near a second end of the elongated body, and the drive member may be configured to rotate within the elongated body and to drive the movable arm along a longitudinal axis of the elongated body toward the second end to separate the tubular structure from the second combustor. | 02-26-2015 |
20150107264 | STRUCTURAL MOUNTING ARRANGEMENT FOR GAS TURBINE ENGINE COMBUSTION GAS DUCT - A gas turbine engine ducting arrangement ( | 04-23-2015 |
20150128610 | FLEXIBLE COMPONENT PROVIDING SEALING CONNECTION - A sealing component ( | 05-14-2015 |
20180023813 | COMPACT MULTI-PIECE SPRING-LOADED CROSSFIRE TUBE | 01-25-2018 |