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公开(公告)号：EP3106646B2
公开(公告)日：2024-07-31
申请号：EP16174862.9
申请日：2016-06-16
CPC分类号： F01D25/12 , F02K3/115 , F02C6/08 , F02C7/14 , F02C9/18 , F05D2260/21320130101 , F05D2260/23120130101 , F05D2270/30320130101 , F02C7/185 , Y02T50/60
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公开(公告)号：EP4394169A1
公开(公告)日：2024-07-03
申请号：EP23216502.7
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Madden, Christopher , Beaven, David , Bemment, Craig , Ferra, Paul , Keeler, Benjamin , Swann, Peter , Yates, Martin
CPC分类号： F02C7/222 , F02C7/224 , F02C7/236 , F02C7/228 , F02C9/40 , F05D2260/9820130101 , F05D2260/21320130101 , F05D2260/20520130101 , F05D2270/30320130101 , F02C7/14 , F02C3/24
摘要： There is provided a method (1000) of operating a gas turbine engine (10). The gas turbine engine (10) comprises a combustor (16) having a plurality of fuel spray nozzles (403, 404) and a fuel system arranged to provide fuel to the combustor (16). The fuel system comprises: a fuel pump (904); a fuel distributing valve (909) downstream of the fuel pump (904) arranged to distribute fuel to the plurality of fuel spray nozzles (403, 404) and bias fuel flow to the nozzles (403, 404) such that a first subset (403) of the plurality of fuel spray nozzles (403, 404) receives more fuel than a second subset (404) of the plurality of fuel spray nozzles (403, 404); and a fuel-oil heat exchanger (903). The method (1000) comprises providing a fuel to the combustor (16) and transferring heat from oil to the fuel in the fuel-oil heat exchanger (903) before the fuel enters the combustor (16) so as to lower a viscosity of the fuel to 0.58 mm2/s or lower on entry to the combustor (16) at cruise conditions. Also provided is a gas turbine engine (10) for an aircraft.
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公开(公告)号：EP4365430A1
公开(公告)日：2024-05-08
申请号：EP23207288.4
申请日：2023-11-01
发明人： PLAMONDON, Etienne
CPC分类号： F02C9/52 , F02C9/54 , F02C9/56 , F02C9/28 , F05D2270/0820130101 , F05D2270/08320130101 , F05D2270/30120130101 , F05D2270/30320130101 , F05D2270/30420130101 , F05D2270/306120130101
摘要： A control method is provided for an engine (22). During this control method, a lambda target parameter indicative of a ratio between a stoichiometric air-to-fuel ratio and an actual air-to-fuel ratio is determined. A control signal is determined using the lambda target parameter. A component (78A) of the engine (22) is operated based on the control signal to regulate airflow within a compressor section (38) of the engine (22).
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公开(公告)号：EP4443050A1
公开(公告)日：2024-10-09
申请号：EP24161493.2
申请日：2024-03-05
CPC分类号： F22D1/36 , F01K17/02 , F01D19/00 , F05D2270/30320130101 , F01D15/10 , F05D2220/7620130101 , F05D2270/08220130101 , F05D2260/232220130101
摘要： A conduit (104) is preheated with steam having steam drain valve(s) (DV1-DV2) therein open to allow draining and control valve(s) (CV1-CV2) therein closed to prevent steam downstream flow. A gas may backfill the conduit (104) from downstream gas source to further preheat, and gas drain valve(s) (DV3-DV4) may be provided to drain the gas. A predicted exit temperature (TE) of the steam or gas for a respective drain valve is calculated using a linear regression model based on initial temperature (Ti) and pressure (Pi) of the steam and a Joule-Thompson cooling effect for the steam or gas at the respective drain valve. The preheating is stopped for the respective section of conduit (104) when one or a combination of the predicted exit temperatures (TE) is greater than or equal to a respective required exit temperature of the steam or gas at a respective drain valve. The method and system may sequentially ensure adequate preheating of sections of the conduit (104).
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公开(公告)号：EP3882449B1
公开(公告)日：2024-09-11
申请号：EP21162962.1
申请日：2021-03-16
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公开(公告)号：EP4390096A1
公开(公告)日：2024-06-26
申请号：EP23216526.6
申请日：2023-12-14
申请人： Rolls-Royce plc
发明人： Madden, Christopher , Bemment, Craig , Ferra, Paul , Keeler, Benjamin , Minelli, Andrea , Swann, Peter , Yates, Martin
CPC分类号： F02C7/224 , F02C7/14 , F02C9/20 , F05D2260/21320130101 , F05D2270/30320130101
摘要： There is provided a method (300) of operating a gas turbine engine (10) having a lean burn staged combustion system having a combustor (16) in which fuel is combusted. The gas turbine engine (10) comprises a fuel-oil heat exchanger (114) arranged to transfer heat between oil and fuel that is provided to the combustor (16). The method (300) comprises transferring heat (301) from the oil to the fuel before the fuel enters the combustor (16) so as to raise the fuel temperature to an average of at least 135°C on entry to the combustor (16) at cruise conditions. Also provided is a gas turbine for an aircraft.
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公开(公告)号：EP4368824A1
公开(公告)日：2024-05-15
申请号：EP23192829.2
申请日：2018-06-18
CPC分类号： F02K5/00 , F02C6/14 , F02C7/32 , F05D2270/10120130101 , F05D2260/4220130101 , F05D2270/05120130101 , F05D2220/7620130101 , F05D2270/30320130101 , Y10S903/903 , Y02T50/60 , B64D27/026
摘要： A hybrid-electric propulsion system 50 includes a turbomachine 102 and an electric machine 56 coupled to the turbomachine 102. A method for operating the hybrid-electric propulsion system 50 includes receiving information indicative of an operability parameter of the turbomachine 102; determining the turbomachine 102 is operating within a predetermined operability range based at least in part of the received information indicative of the operability parameter of the turbomachine 102; and operating the hybrid electric propulsion system 50 in an electric generation mode to generate electric power with the electric machine 56 in response to determining the turbomachine 102 is operating within the predetermined operability range.
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公开(公告)号：EP3593046B1
公开(公告)日：2024-09-18
申请号：EP18701597.9
申请日：2018-01-12
IPC分类号： F23N1/00 , F23N1/02 , F23D14/32 , F23L7/00 , F23N3/00 , F02C9/28 , F02C9/40 , F02C3/20 , F02C3/30 , F23N5/24
CPC分类号： F02C3/20 , F02C3/30 , F02C9/28 , F02C9/40 , F23L7/007 , F23N1/00 , F23N3/00 , F23N5/24 , F23D14/32 , F23C2900/9901120130101 , F23L2900/0700120130101 , F23L2900/0700320130101 , F23L2900/0700520130101 , F23L2900/0700620130101 , F23L2900/0700720130101 , F05D2270/30320130101 , F23N1/02 , F23N2221/0620200101 , F23N2221/0820200101 , F23N2237/0820200101 , F23N2241/2020200101 , Y02E20/32
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9.发明公开
公开(公告)号：EP4421327A2
公开(公告)日：2024-08-28
申请号：EP24186233.3
申请日：2016-07-07
IPC分类号： F04D29/58
CPC分类号： F04D17/12 , F04D27/0207 , F04D27/0215 , F04D29/5826 , F05D2270/30320130101 , F25J1/0055 , F25J1/0291 , F25J1/0298 , F25J1/0236 , F04D27/0223 , F05B2270/30320130101 , F25J1/0022 , F25J1/0052 , F25J2280/0220130101 , F25J2280/2020130101
摘要： A compressor system (1) is described, comprising:
- at least a first compressor (7) having a suction side (7S) and a delivery side (7D);
- an anti-surge line (23);
- an anti-surge valve (25) arranged along the anti-surge line (23) and controlled for recirculating a gas flow from the delivery side (7D) back to the suction side (7S) of the compressor (7);
- a heat removal arrangement (61; 68; 70) between the anti-surge valve (23) and the suction side (7S) of the compressor (7).-
公开(公告)号：EP3983864B1
公开(公告)日：2024-07-31
申请号：EP20742334.4
申请日：2020-06-12
CPC分类号： B64D13/006 , G05D16/185 , F02C6/08 , F05D2270/6520130101 , F05D2270/30320130101 , Y02T50/50
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