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公开(公告)号：US11530646B2
公开(公告)日：2022-12-20
申请号：US17176803
申请日：2021-02-16
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：US20210355866A1
公开(公告)日：2021-11-18
申请号：US17383512
申请日：2021-07-23
摘要： A propulsor section includes a propulsor having a plurality of blades rotatable about an engine longitudinal axis. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a low pressure turbine that drives the propulsor through an epicyclic gear arrangement, and includes a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor. The power ratio is defined by the second power input divided by the first power input. The power ratio is equal to, or greater than, 1.0 and less than, or equal to, 1.4.
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公开(公告)号：US20210348556A1
公开(公告)日：2021-11-11
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：US11136899B2
公开(公告)日：2021-10-05
申请号：US16900168
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 example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.
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公开(公告)号：US20230175433A1
公开(公告)日：2023-06-08
申请号：US17897870
申请日：2022-08-29
CPC分类号： F02C3/04 , F02K3/075 , F01D25/24 , F01D25/162 , F01D25/28 , F02K3/06 , F01D9/023 , F05D2240/12 , F05D2240/24 , Y02T50/60
摘要： A gas turbine engine includes a propulsor. A speed reduction device is drivingly connected to the propulsor. A compressor section with a high pressure compressor has between 8 and 13 stages and a pressure ratio of at least 16:1 and less than 35:1. A turbine section including a transition duct is located between a high pressure turbine and a low pressure turbine including fewer support struts than vanes in a first vane row of the low pressure turbine. The first vane row of the low pressure turbine is located downstream of the transition duct and downstream of a first row of blades in the low pressure turbine. The first row of blades in the low pressure turbine are immediately downstream of the support struts.
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26.发明公开公开(公告)号：US20230167752A1
公开(公告)日：2023-06-01
申请号：US18104375
申请日：2023-02-01
发明人： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
CPC分类号： F01D25/164 , F02K3/06 , F02C3/107 , F01D15/12 , F01D25/162 , F02C7/06 , F02C7/20 , F02C7/36 , F05D2220/32 , F05D2240/60 , F05D2260/40311
摘要： A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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公开(公告)号：US20230160337A1
公开(公告)日：2023-05-25
申请号：US17898728
申请日：2022-08-30
CPC分类号： F02C3/107 , F01D25/16 , F02K3/06 , F02C7/36 , F05D2260/40 , F05D2260/40311 , F05D2220/327
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：US11613998B2
公开(公告)日：2023-03-28
申请号：US17465251
申请日：2021-09-02
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 example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.
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公开(公告)号：US11578651B2
公开(公告)日：2023-02-14
申请号：US17383512
申请日：2021-07-23
摘要： A propulsor section includes a propulsor having a plurality of blades rotatable about an engine longitudinal axis. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a low pressure turbine that drives the propulsor through an epicyclic gear arrangement, and includes a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor. The power ratio is defined by the second power input divided by the first power input. The power ratio is equal to, or greater than, 1.0 and less than, or equal to, 1.4.
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公开(公告)号：US20220082065A1
公开(公告)日：2022-03-17
申请号：US17538048
申请日：2021-11-30
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section, a compressor section including a low pressure compressor and a second compressor section, and a turbine section including a low pressure turbine and a high pressure turbine. The low pressure turbine drives the low pressure compressor and the gear arrangement to drive the propulsor. A core split power ratio is provided by power input to the high pressure compressor divided by a power input to the low pressure compressor measured in horsepower.
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