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1. 发明授权

US11835236B1 Combustor with reverse dilution air introduction 有权
公开(公告)号：US11835236B1
公开(公告)日：2023-12-05
申请号：US17857657
申请日：2022-07-05
申请人： General Electric Company
发明人： Hiranya Kumar Nath , Ravindra Shankar Ganiger , Steven Clayton Vise
IPC分类号： F23R3/54 , F23R3/00 , F23R3/06
CPC分类号： F23R3/54 , F23R3/002 , F23R3/06 , F05D2240/35
摘要： A combustor for a gas turbine engine includes a forward liner segment having an aft end portion. The forward liner segment at least partially defines a primary combustion chamber. The combustor further includes an aft liner segment having a forward end portion. A channel is defined between the forward liner segment and the aft liner segment. The channel directs a stream of dilution air in a counter-flow or reverse direction with respect to combustion gases flowing from the primary combustion chamber during operation of the combustor.

2. 发明公开

US20230167975A1 FUEL NOZZLE WITH RESTRICTED CORE AIR PASSAGE 审中-公开
公开(公告)号：US20230167975A1
公开(公告)日：2023-06-01
申请号：US17535852
申请日：2021-11-26
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Tin-Cheung John HU
IPC分类号： F23R3/54 , F02C3/04 , F02C3/14 , F02C7/18 , F02C7/24 , F23C9/00 , F23M20/00 , F23R3/06 , F23R3/14 , F23R3/20 , F23R3/24 , F23R3/28 , F23R3/34 , F23R3/44
CPC分类号： F23R3/54 , F02C3/04 , F02C3/145 , F02C7/18 , F02C7/24 , F23C9/006 , F23M20/005 , F23R3/06 , F23R3/14 , F23R3/20 , F23R3/24 , F23R3/286 , F23R3/343 , F23R3/44 , F05D2220/32 , F23R2900/00014 , F23R2900/00015 , F23R2900/03042
摘要： A fuel nozzle for a combustor of an aircraft engine includes a nozzle body defining an a fuel passage, extending therethrough between a fuel inlet and a fuel outlet located at the outlet end that at least partially defines a nozzle tip, for directing a fuel flow into the combustor via the nozzle tip. A core air passage extends through the nozzle body for directing a core air flow into the combustor via the nozzle tip. At least two flow restrictors are disposed in series within the core air passage, the flow restrictors including an upstream flow restrictor and a downstream flow restrictor each having an orifice therein. The restricted air flow passage having a cross-sectional area smaller than that of the core air passage. The orifice in the upstream flow restrictor being at least partially offset from the orifice in the downstream flow restrictor.

3. 发明授权

US11248796B2 Gas turbine engine 有权
公开(公告)号：US11248796B2
公开(公告)日：2022-02-15
申请号：US16802738
申请日：2020-02-27
申请人： HONDA MOTOR CO., LTD.
发明人： Yasuhara Kamoi , Hiroshi Sawamura
IPC分类号： F23R3/54 , F23R3/60
摘要： In a gas turbine engine, an inside turn duct portion and a nozzle guide vane are engaged together via an engagement part. An axially forward-facing load acting on a reverse flow combustor is transmitted to the vane via the engagement part. Therefore, it is possible to counteract an axially backward-facing load acting on the vane from combustion gas with the axially forward-facing load, thus reducing a bending moment acting on a support part of the vane and enhancing durability. Furthermore, part of the axially forward-facing load acting on the combustor acts on the support part via the vane. The axially forward-facing load acting on the support part of the combustor without via the vane is decreased by the above-mentioned part. Thus, it is possible to reduce bending moments acting on an outside turn duct portion and dome portion of the combustor and enhance durability, thereby preventing degradation of combustion performance.

4. 发明授权

US11156156B2 Gas turbine engine with a unitary structure and method for manufacturing the same 有权
公开(公告)号：US11156156B2
公开(公告)日：2021-10-26
申请号：US16151728
申请日：2018-10-04
申请人： United Technologies Corporation
发明人： Lawrence Binek , Jesse R. Boyer , Om P. Sharma , Evan Butcher , Bryan G. Dods , Vijay Narayan Jagdale
IPC分类号： F02C7/22 , F02K3/10 , B33Y80/00 , F23R3/20 , F02C3/05 , F02C3/14 , F23R3/34 , F23R3/54
摘要： A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.

5. 发明申请

US20210041106A1 REVERSE FLOW COMBUSTOR 有权
公开(公告)号：US20210041106A1
公开(公告)日：2021-02-11
申请号：US17072465
申请日：2020-10-16
申请人： Massimo Giovanni Giambra , Joseph Douglas Monty , Stephen John Howell
发明人： Massimo Giovanni Giambra , Joseph Douglas Monty , Stephen John Howell
IPC分类号： F23R3/54 , F23R3/06
摘要： An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

6. 发明申请

US20200284433A1 GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20200284433A1
公开(公告)日：2020-09-10
申请号：US16802738
申请日：2020-02-27
申请人： HONDA MOTOR CO., LTD.
发明人： Yasuhara Kamoi , Hiroshi Sawamura
IPC分类号： F23R3/54 , F23R3/60
摘要： In a gas turbine engine, an inside turn duct portion and a nozzle guide vane are engaged together via an engagement part. An axially forward-facing load acting on a reverse flow combustor is transmitted to the vane via the engagement part. Therefore, it is possible to counteract an axially backward-facing load acting on the vane from combustion gas with the axially forward-facing load, thus reducing a bending moment acting on a support part of the vane and enhancing durability. Furthermore, part of the axially forward-facing load acting on the combustor acts on the support part via the vane. The axially forward-facing load acting on the support part of the combustor without via the vane is decreased by the above-mentioned part. Thus, it is possible to reduce bending moments acting on an outside turn duct portion and dome portion of the combustor and enhance durability, thereby preventing degradation of combustion performance.

7. 发明授权

US10697634B2 Inner cooling shroud for transition zone of annular combustor liner 有权
公开(公告)号：US10697634B2
公开(公告)日：2020-06-30
申请号：US15914669
申请日：2018-03-07
申请人： General Electric Company
发明人： Daniel Haeny , Pirmin Schiessel , Martin Zajadatz , Thomas Christen
IPC分类号： F23R3/00 , F01D9/02 , F23R3/50 , F23R3/54
摘要： An annular combustor includes an inner liner shell and an outer liner shell defining an interior volume through which combustion gases flow in a gas flow direction from a forward end to an aft end. A cooling shroud is attached radially outward of the inner liner shell, forming a cooling passage between the inner liner shell and the cooling shroud. The cooling passage directs air in an air flow direction opposite to the gas flow direction. The cooling shroud is assembled from circumferentially adjoined cooling shroud segments, and the distance between the cooling shroud segments and the inner liner shell is greater at the forward end than at the aft end. Fastening elements are distributed across an axial length of the cooling shroud segments in circumferentially staggered rows. Each forwardmost fastening element is disposed immediately adjacent to a curved portion at the forward end of each respective cooling shroud segment to reduce vibration.

8. 发明授权

US10344981B2 Staged dual fuel radial nozzle with radial liquid fuel distributor 有权
公开(公告)号：US10344981B2
公开(公告)日：2019-07-09
申请号：US15382112
申请日：2016-12-16
申请人： Delavan Inc
发明人： Lev Alexander Prociw , Jason A. Ryon
IPC分类号： F23R3/10 , F23R3/14 , F23R3/28 , F23R3/36 , F23D11/38 , F23D14/24 , F23R3/34 , F23R3/54 , F23D11/10
摘要： A nozzle includes a nozzle body defining a longitudinal axis and including a primary distributor and a secondary distributor. The primary distributor has an inner air passage fed by a radial swirler; a first fuel circuit radially outboard from the inner air passage with respect to the longitudinal axis; a second fuel circuit radially outboard from the first fuel circuit with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet; and an outer air passage defined between a fuel circuit outer wall and an outer air passage wall, wherein the outer air passage is a converging non-swirling outer air passage. The secondary distributor similar to the primary distributor is downstream of the primary distributor with respect to the longitudinal axis.

9. 发明申请

US20190032920A1 REVERSE FLOW COMBUSTOR 审中-公开
公开(公告)号：US20190032920A1
公开(公告)日：2019-01-31
申请号：US16020312
申请日：2018-06-27
申请人： GE Avio S.r.l. , General Electric Company
发明人： Massimo Giovanni Giambra , Joseph Douglas Monty , Stephen John Howell
IPC分类号： F23R3/54 , F02C3/14 , F23R3/06 , F23R3/46 , F02C7/18
CPC分类号： F23R3/54 , F02C3/145 , F02C7/18 , F23R3/06 , F23R3/46
摘要： An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.

10. 发明授权

US10139108B2 D5/D5A DF-42 integrated exit cone and splash plate 有权
公开(公告)号：US10139108B2
公开(公告)日：2018-11-27
申请号：US14732954
申请日：2015-06-08
申请人： Siemens Energy, Inc.
发明人： Richard L. Thackway , Charalambos Polyzopoulos, Jr. , James M. Hurney
IPC分类号： F23R3/00 , F23R3/06 , F01D9/02 , F23R3/60 , F02C3/14 , F23R3/54
摘要： A combustor basket assembly for a gas turbine engine that includes a combustor basket having a basket liner including an input end and an output end. An integrated exit cone and splash plate member is affixed to the output end of the basket liner and includes a base portion, an exit cone portion and a splash plate portion. The base portion includes an annular cooling channel that receives a cooling air flow and the exit cone portion and the splash plate portion each include an array of cooling feed holes in fluid communication with the cooling channel. The spacing between the feed holes and the size of the feed holes can be optimized to provide more cooling for hotter regions.

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