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公开(公告)号：EP4368825A2
公开(公告)日：2024-05-15
申请号：EP24167721.0
申请日：2021-02-18
Applicant: RTX Corporation
Inventor： CAI, Chaohong , MEISNER, Richard P. , CROWLEY, Timothy J. , MA, David Lei
IPC: F02C9/28
CPC classification number: F02C9/28 , F05D2220/32920130101 , F02C3/10 , F05D2270/30420130101 , F05D2270/33520130101 , F05D2200/1220130101 , F05D2200/21120130101
Abstract: A turboshaft engine for a helicopter, comprising: a gas generator (102; 202); a power turbine (104) disposed downstream of the gas generator (102; 202); and a controller (132; 232) in communication with the gas generator (102; 202) and the power turbine (104), the controller (132; 232) including a processor (134) configured to receive a collective lever angle command signal and a real-time power turbine speed signal, generate a power turbine speed rate signal based at least in part on the collective lever angle command signal and the real-time power turbine speed signal, generate a power turbine torque request signal based at least in part on the collective lever angle command signal and the real-time power turbine speed signal, generate a fuel flow signal and an inlet guide vane signal (254) based at least in part on the power turbine speed rate signal, and send the fuel flow signal and the inlet guide vane signal (254) to the gas generator (102; 202) in order to control a torque of the power turbine (104).
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公开(公告)号：EP3913201B1
公开(公告)日：2024-05-15
申请号：EP21157924.8
申请日：2021-02-18
CPC classification number: F02C9/28 , F05D2220/32920130101 , F02C3/10 , F05D2270/30420130101 , F05D2270/33520130101 , F05D2200/1220130101 , F05D2200/21120130101
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公开(公告)号：EP3045696B1
公开(公告)日：2018-09-05
申请号：EP16151976.4
申请日：2016-01-19
Applicant: United Technologies Corporation
Inventor： CAI, Chaohong
CPC classification number: F02C9/54 , F02C3/10 , F05D2220/329 , F05D2270/021 , F05D2270/052 , F05D2270/101 , F05D2270/304 , F05D2270/335 , F05D2270/44 , F05D2270/705
Abstract: A control system for a gas turbine engine including a power turbine is disclosed. The control system may also include an outer loop control module to determine a torque request. The outer loop control module may include a feedback control component operative to provide regulation of the power turbine, a feed-forward component operative to anticipate a load on the power turbine, and a hybrid control component operative to prevent output of a torque request that cannot currently be delivered by the power turbine. The control system may also include an inner loop control module to receive the torque request from the outer loop control module, to determine fuel flow and inlet guide vane schedules based at least in part on the received torque request, and to send signals to a gas generator of the gas turbine engine in order to control the gas generator according to the determined fuel flow and inlet guide vane schedules.
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公开(公告)号：EP3361073A1
公开(公告)日：2018-08-15
申请号：EP18156187.9
申请日：2018-02-09
Applicant: Pratt & Whitney Canada Corp.
Inventor： FOREST, Jean-Jacques , POULIN, Martin
CPC classification number: F02C7/36 , F02C3/10 , F02C7/268 , F02C7/32 , F05D2220/323 , F05D2260/40 , F05D2260/85
Abstract: A gas turbine engine (10) has a LP spool (20) including an LP shaft (23) and a HP spool (40) including an HP shaft (43), an accessory gear box (AGB) (50) drivingly engaged to a plurality of accessories, an engine starter (52B) drivingly engaged to the AGB (50), and a drive shaft (30) drivingly engaged to the AGB (50). In a first engine mode, the drive shaft (30) is drivingly engaged to the HP shaft (43) and is disengaged from the LP shaft (23), the engine starter (52B) is in driving engagement with the HP shaft (43) via the drive shaft (30), and the LP shaft (23) is disengaged from the AGB (50). In a second engine mode, the drive shaft (30) is drivingly engaged to the LP shaft (23) and is disengaged from the HP shaft (43), the LP shaft (23) is in driving engagement with the AGB (50) via the drive shaft (30), and the HP shaft (43) is disengaged from the AGB (50).
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公开(公告)号：EP3354866A1
公开(公告)日：2018-08-01
申请号：EP18153400.9
申请日：2018-01-25
Applicant: Nuovo Pignone Tecnologie SrL
Inventor： RUSSO, Alessandro , DEL BONO, Alessandro , MEI, Luciano , CIOFINI, Maurizio , SHAMIM, Abdus , BALADI, Mehdi Milani , POSTACCHINI, Alessio , DUMM, Bernard W. , HAYDEN, Jason , CARTOCCI, Gabriele , CARATELLI, Francesco
IPC: F01D25/28
CPC classification number: F02C3/10 , F01D25/28 , F01D25/285 , F02C7/143 , F05D2240/54 , F05D2240/91 , F05D2260/207 , F16M1/04 , F16M5/00 , F25J1/0022 , F25J1/0052 , F25J1/0055 , F25J1/0082 , F25J1/0085 , F25J1/0087 , F25J1/0209 , F25J1/0214 , F25J1/0216 , F25J1/0217 , F25J1/0283 , F25J1/029 , F25J1/0292 , F25J1/0294 , Y02T50/671
Abstract: The gas turbine system (1) comprises an aeroderivative gas turbine engine (2) and a load (3) having a shaft line (6) drivingly coupled to the gas turbine engine (2). The gas turbine engine (2) comprises a high-pressure turbine section (61) and a high-pressure compressor section (19), drivingly coupled to one another by a first turbine shaft (91). The gas turbine engine (2) further comprises an intermediate-pressure turbine section (63) and a low-pressure compressor section (17), drivingly coupled to one another by a second turbine shaft (92), coaxial to the first turbine shaft (91). Furthermore, a combustor section (13) is provided, fluidly coupled to the high-pressure compressor section (19) and to the high-pressure turbine section (61). A free power turbine (81), supported by a third turbine shaft (93) which is mechanically uncoupled from the first turbine shaft (91) and the second turbine shaft (92), and is directly coupled to the shaft line (6), such that the shaft line (6) and the third turbine shaft (93) rotate at the same rotational speed. The free power turbine is adapted to generate a mechanical power rating of at least 65MW under ISO day conditions.
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公开(公告)号：EP2145080B1
公开(公告)日：2018-08-01
申请号：EP08788124.9
申请日：2008-04-04
Applicant: Safran Helicopter Engines
Inventor： HAEHNER, Edgar , SENGER, Gérald
CPC classification number: F02C7/32 , F01D15/08 , F01D15/10 , F02C3/10 , F02C7/26 , F05D2220/329 , F05D2260/85 , F05D2260/90 , F05D2260/903
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公开(公告)号：EP3351766A1
公开(公告)日：2018-07-25
申请号：EP18153071.8
申请日：2018-01-23
Applicant: United Technologies Corporation
Inventor： KUPRATIS, Daniel Bernard , HANRAHAN, Paul R.
CPC classification number: F02C7/36 , F02C3/10 , F02C3/113 , F02C9/20 , F02C9/26 , F02K3/06 , F04D27/002 , F05D2220/323 , F05D2260/40311 , F16H1/28
Abstract: A gas turbine engine (20;120) comprises a fan rotor (122) driven by a fan drive turbine (124), the fan drive turbine (124) also rotating with one of a ring gear (130), an intermediate gear carrier (152), and a sun gear (138). A first compressor (140) is driven by another of the ring gear (130), the intermediate gear carrier (152), and the sun gear (138). A second turbine (136) rotates with the third of the ring gear (130), the intermediate gear carrier (152), and the sun gear (138).
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公开(公告)号：EP2256036B1
公开(公告)日：2018-07-25
申请号：EP10159995.9
申请日：2010-04-15
Applicant: Rolls-Royce plc
Inventor： Harris, Paul Jeremy Hugh , Hewitt, Frank Anthony , Johnson, Martin Christopher , Wright, Christopher
CPC classification number: B64C29/0016 , B64C15/14 , B64C29/0075 , B64D2027/026 , F02C3/10 , F02K1/004 , F02K5/00 , F05D2220/328 , F05D2220/76 , Y02T50/671
Abstract: An aircraft comprises a lift/propulsion unit 8 which comprises a power unit such as a turboshaft engine 14 which drives a fan 10 through a transmission mechanism 16. The fan 10 discharges to vectoring nozzles 24 which can be independently swivelled to provide lift or propulsion thrust. An output shaft 20 of the transmission mechanism 16 serves as the main shaft of a motor/generator 26 of modular form. The motor/generator 26 can act as a generator to charge an electrical storage device such as a battery 32, or as a motor to drive the fan 10, either alone or to supplement the output of the engine 14. Reaction control nozzles 38 are provided at extremities of the aircraft to provide stabilising thrust. The aircraft is capable of vertical take off and hovering, with the vectoring nozzles 24 swivelled to a lift position, and forward thrust with the vectoring nozzles 24 swivelled to a propulsion position.
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公开(公告)号：EP2587039B1
公开(公告)日：2018-04-11
申请号：EP12189326.7
申请日：2012-10-19
Applicant: United Technologies Corporation
Inventor： Kupratis, Daniel B.
CPC classification number: F02K3/12 , F02C3/10 , F02C3/107 , F02C6/02 , F02C7/36 , F02K3/04 , F02K3/077
Abstract: A method of operating a propulsion system (14) includes powering an auxiliary fan (18) with a gas turbine engine (20), where the auxiliary fan (18) is along an auxiliary axis (F) and the gas turbine engine (20) is along an engine axis (F), the auxiliary axis (F) being parallel to the engine axis (A).
