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| Number | Title | Issue Date |
| 8171740 | Annular rich-quench-lean gas turbine combustors with plunged holes A combustor may include an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor may further include an inner liner having a second group of air admission holes and defining a plurality of inner liner ... | 05/08/2012 |
| 8146372 | Gas turbine combustion chamber having inner and outer walls subdivided into sectors An annular combustion chamber has an inner wall and an outer wall of ceramic matrix composite material, together with a chamber end wall that is connected to the inner and outer walls. Elastically-deformable link elements connect the inner wall and the outer chamber... | 04/03/2012 |
| 8141371 | Gas turbine combustion chamber made of CMC material and subdivided into sectors An assembled annular combustion chamber comprises an annular inner wall and an annular outer wall made of ceramic matrix composite material together with a chamber end wall connected to the inner and outer walls and provided with orifices for receiving injectors. El... | 03/27/2012 |
| 8056346 | Combustor A combustor includes a first wall, a second wall, an injector grommet, a combustor longitudinal axis, and a connection assembly indirectly connecting the first wall to the second wall. A portion of the injector grommet is disposed within a groove of the connection a... | 11/15/2011 |
| 8015829 | Combustor A gas turbine engine combustor has forward bulkhead extending between inboard and outboard walls and cooperating therewith to define a combustor interior volume or combustion chamber. At least one of the walls has an exterior shell and an interior shell including a ... | 09/13/2011 |
| 8001793 | Gas turbine engine reverse-flow combustor A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple rows of effusion cooling holes, bounded by cooled effusionless bands... | 08/23/2011 |
| 7886545 | Methods and systems to facilitate reducing NOemissions in combustion systems A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer wall is orientated substantially parallel to the center axis. The me... | 02/15/2011 |
| 7856830 | Noise reducing combustor A combustor having liners with a plurality of angled effusion holes defined therethrough at a first angle with respect to a surface of the liners and at a second angle with respect to a corresponding radial plane. A density of the effusion holes defined in a primary... | 12/28/2010 |
| 7849696 | Assembling an annular combustion chamber of a turbomachine An annular combustion chamber comprising axial walls interconnected by a chamber end wall having a coefficient of thermal expansion that is different from that of the axial walls, the chamber end wall being provided with a plurality of inner and outer fastener tabs ... | 12/14/2010 |
| 7703290 | Air thrust bearing for a gas turbine engine A gas turbine engine comprises a rotary compressor (6) which is subject to forward thrust forces and is mounted on an axial shaft (50) which has a forward facing surface (67) located in a thrust bearing (52). A bleed of air under pressure... | 04/27/2010 |
| 7549294 | Turbomachine with angular air delivery A turbomachine assembly comprising: an annular compression section; a casing formed by an outer annular shell (204) and an inner annular shell (206) secured inside the outer shell by means of a plurality of radial support arms (208); an annular ... | 06/23/2009 |
| 7509813 | Combustor heat shield A heat shield for a gas turbine engine combustor includes an apparatus for providing a spiral flow to improve at least the cooling of the heat shield. ... | 03/31/2009 |
| 7412834 | Annular combustion chamber for a turbomachine with an improved inner fastening flange An annular combustion chamber for a turbomachine comprises inner and outer annular walls united by a transverse wall, the inner and outer walls are extended at their downstream ends by inner and outer fastener flanges for fastening respectively to inner and outer sh... | 08/19/2008 |
| 7360364 | Method and apparatus for assembling gas turbine engine combustors A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled toge... | 04/22/2008 |
| 7350358 | Exit duct of annular reverse flow combustor and method of making the same A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbi... | 04/01/2008 |
| 7328582 | Annular combustion chamber for a turbomachine An annular turbine engine combustion chamber configured so that in an axial half-section, values of first acute angles formed between a line that is effectively the median of the half-section located between an external axial wall and an internal axial wall, and the... | 02/12/2008 |
| 7318317 | Combustion chamber for a gas turbine A combustion chamber 10 for a gas turbine that operates in a highly diluted mode of combustion has a substantially toroidal plenum 30. At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the dis... | 01/15/2008 |
| 7308794 | Combustor and method of improving manufacturing accuracy thereof An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and an interior directly exposed to a combustion region of the combustor... | 12/18/2007 |
| 7302802 | Aerodynamic trip for a combustion system A apparatus and method for improving combustion by improving at least one of temperature distribution in the combustor, pressure distribution around the combustor and combustion noise level in the combustor, by redistributing air around the combustor to modify the s... | 12/04/2007 |
| 7299622 | Component for being subjected to high thermal load during operation and a method for manufacturing such a component Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) tha... | 11/27/2007 |
| 7269958 | Combustor exit duct A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions. ... | 09/18/2007 |
| 7270175 | Extended impingement cooling device and method An extended impingement cooling structure to cool outside an air supply plenum comprises an inner wall; an impingement sheet; a series of supports to maintain the inner wall in spaced relation to the impingement sheet, and a baffle supported between the inner wall a... | 09/18/2007 |
| 7260936 | Combustor having means for directing air into the combustion chamber in a spiral pattern A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral patter... | 08/28/2007 |
| 7251942 | Integrated gearless and nonlubricated auxiliary power unit An auxiliary power unit (APU) includes a compressor, a turbine, a combustor, and a starter-generator unit all integrated within a single containment housing. The turbine has an output shaft on which the compressor is mounted, and the starter-generator unit is couple... | 08/07/2007 |
| 7222488 | Fabricated cowl for double annular combustor of a gas turbine engine A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slo... | 05/29/2007 |
| 7224082 | Turbomachine including an integrated electricity generator A turbomachine includes a high-pressure spool, an axial compressor of axis X mounted on a rotor and including a casing and at least one rear bearing disposed between the casing and the rotor of the compressor. The turbomachine further includes an electricity generat... | 05/29/2007 |
| 7219490 | Nested core gas turbine engine A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section. ... | 05/22/2007 |
| 7200987 | Off-axis pulse detonation configuration for gas turbine engine The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation ... | 04/10/2007 |
| 7194866 | Static structure for an expendable gas turbine engine A static structure for a miniature gas turbine engine includes a forward housing, a forward cover, a diffuser housing, a diffuser, a turbine nozzle, a combustor liner, a combustor housing and an exhaust pipe with relatively uncomplicated assembly interfaces. The sta... | 03/27/2007 |
| 7191665 | Support for a reflective target A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating te... | 03/20/2007 |
| 7168949 | Stagnation point reverse flow combustor for a combustion system A combustor assembly includes a combustor vessel having a wall, a proximate end defining an opening and a closed distal end opposite said proximate end. A manifold is carried by the proximate end. The manifold defines a combustion products exit. The combustion produ... | 01/30/2007 |
| 7155800 | Automated seal strip assembly method and apparatus for rotary machines A automated sealing assembly for rotary machines including: a seal guide assembly, the seal guide assembly aligns and holds a caulk wire and a sealing strip in a rotor groove for peening; a peening tool, the peening tool peens said caulk wire to deform the caulk wir... | 01/02/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7146816 | Effusion momentum control A combustor liner for shielding an engine from heat generated in a combustion zone includes a sheet with a cool surface for intercepting a cooling air stream and a hot surface enclosing the combustion zone, the combustor liner further including an array of effusion ... | 12/12/2006 |
| 7140185 | Heatshielded article A heatshielded article includes a support 18 and at least one heatshield 20 secured adjacent to the support. The heatshield includes a shield portion 28 spaced from the support. The shield portion includes a hot side 30 and an uncoated co... | 11/28/2006 |
| 7134286 | Gas turbine floating collar arrangement A simplified floating collar mounting arrangement for receiving a fuel nozzle swirler body of a gas turbine engine combustor is provided. The assembly comprises a floating collar mounted between a spaced-apart mounting flange and cap, and slidably trapped therebetwe... | 11/14/2006 |
| 7127897 | Combustion chamber A combustion chamber 10 for a gas turbine operates in a highly diluted mode of combustion has a substantially toroidal plenum 30. At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposit... | 10/31/2006 |
| 7124487 | Method for controlling carbon formation on repaired combustor liners A method for controlling combustor liner carbon formation on repaired combustors includes making modular effusion panel subassemblies remote from the combustor liner; removing a non-effusion or damaged panel from the combustor liner; and replacing the non-effusion o... | 10/24/2006 |
| 7124588 | Combustion chamber of gas turbine with starter film cooling A combustion chamber of a gas turbine includes starter film cooling of a combustion chamber wall 4 and several circularly arranged burners 7 with local maxima and minima in the intensity of the starter film 3 being provided around the circumfere... | 10/24/2006 |
| 7121095 | Combustor dome assembly of a gas turbine engine having improved deflector plates A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings forme... | 10/17/2006 |
