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公开(公告)号：US20230212981A1
公开(公告)日：2023-07-06
申请号：US17976254
申请日：2022-10-28
CPC分类号： F02C7/18 , F02C3/13 , F02C6/02 , F05D2260/20 , F05D2220/329
摘要： A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.
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公开(公告)号：US11597527B2
公开(公告)日：2023-03-07
申请号：US17376675
申请日：2021-07-15
IPC分类号： F02C6/14 , B64D27/24 , B64D27/10 , F01D15/10 , F02C7/36 , H02K7/18 , B64D27/02 , F02C6/02 , F02C3/107
摘要： An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US20220403788A1
公开(公告)日：2022-12-22
申请号：US17730782
申请日：2022-04-27
摘要： A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a low pressure compressor and a high pressure compressor, a geared architecture, a turbine section including a low pressure turbine and a high pressure turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.
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公开(公告)号：US11448125B2
公开(公告)日：2022-09-20
申请号：US16999408
申请日：2020-08-21
摘要： A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a high pressure turbine having a first stage and a second stage, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; a high pressure compressor connected to a high pressure compressor spool; and a differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear connected to the high pressure compressor spool.
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公开(公告)号：US11448124B2
公开(公告)日：2022-09-20
申请号：US17192039
申请日：2021-03-04
摘要： A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.
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公开(公告)号：US11408343B1
公开(公告)日：2022-08-09
申请号：US17313618
申请日：2021-05-06
IPC分类号： F02K3/02 , F02K3/077 , F02K3/11 , F02C7/36 , F02C7/052 , B64D27/10 , F02C6/20 , F02C9/18 , B64C27/12
摘要： A turboshaft engine includes a core section extending between an inlet and an outlet of the turboshaft engine. The core section includes a compressor, a main combustor, and a main turbine, such that combustion products from the main combustor drives rotation of the turbine and the compressor. A power turbine is fluidly connected to the main turbine and driven by exhaust from the main turbine. A primary bypass is fluidly connected to the inlet and the outlet. The primary bypass directs a portion of an airflow entering the inlet around the core section to the outlet. A secondary bypass is located in the core section and is configured to divert a portion of a core airflow of the core section around the main combustor and the main turbine to the power turbine.
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公开(公告)号：US11326467B2
公开(公告)日：2022-05-10
申请号：US16900199
申请日：2020-06-12
摘要： A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The compressor section includes a compressor electric motor that is electrically coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to a geared architecture to supplement power driving the fan section. A turbine generator driven by a portion of the turbine section provides electric power to the turbine electric motor.
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公开(公告)号：US11286856B2
公开(公告)日：2022-03-29
申请号：US16357392
申请日：2019-03-19
IPC分类号： F02C7/14 , F02C7/143 , F01D9/04 , F02C7/12 , F02C7/18 , F02C9/18 , F02C3/13 , F02C3/32 , F02C7/10
摘要： A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages.
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公开(公告)号：US20220056870A1
公开(公告)日：2022-02-24
申请号：US17350767
申请日：2021-06-17
摘要： A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, a first electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft, and an electric compressor extending along a second axis that is radially offset from the central longitudinal axis, the electric compressor in fluid communication with the second turbine section.
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公开(公告)号：US20220025823A1
公开(公告)日：2022-01-27
申请号：US17493002
申请日：2021-10-04
摘要： A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.
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