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1.发明授权公开(公告)号：US11598223B2
公开(公告)日：2023-03-07
申请号：US16227271
申请日：2018-12-20
发明人： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
摘要： A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. 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：US11448123B2
公开(公告)日：2022-09-20
申请号：US14734035
申请日：2015-06-09
摘要： A gas turbine engine includes a fan bypass ratio greater than 12. A speed reduction device includes a gear ratio of at least 2.6. A turbine section includes a transition duct that is located between a high pressure turbine and a low pressure turbine and includes fewer support struts than vanes in a first vane row of the low pressure turbine.
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公开(公告)号：US11428241B2
公开(公告)日：2022-08-30
申请号：US15136416
申请日：2016-04-22
摘要： An improved stator assembly is disclosed. The stator assembly may comprise an exit guide vane, an OD ring, and an ID ring. The exit guide vane may couple at one end to the OD ring and at an opposite end to the ID ring. The exit guide vane may comprise a leading edge opposite of a trailing edge. The OD ring and the ID ring may couple to a diffuser assembly of a gas turbine engine. The stator assembly may further comprise an aft OD seal, a forward OD seal, an ID seal, and a diffuser assembly seal to reduce airflow leaks around the stator assembly.
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公开(公告)号：US11215120B2
公开(公告)日：2022-01-04
申请号：US15424927
申请日：2017-02-06
摘要： A gas turbine engine comprises a compressor section and a turbine section, the compressor section having a last compressor stage. High pressure cooling air is tapped from a location downstream of the last compressor stage and passed through a heat exchanger. Lower pressure air passes across the heat exchanger to cool the high pressure cooling air. A housing surrounds the compressor section and the turbine section and there being a space radially outwardly of the housing, and a mixing chamber received in the space radially outwardly of the housing, the mixing chamber receiving the high pressure cooling air downstream of the heat exchanger, and further receiving air at a temperature higher than a temperature of the high pressure cooling air downstream of the heat exchanger. Mixed air from the mixing chamber is returned into the housing and utilized to cool at least the turbine section.
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公开(公告)号：US10906657B2
公开(公告)日：2021-02-02
申请号：US16012047
申请日：2018-06-19
IPC分类号： B64D27/02 , B64D27/12 , B64D27/24 , B64D31/14 , B64D33/04 , F02C6/20 , B64D31/02 , H02K7/18 , H02K7/20 , H02K11/00 , F02C6/14
摘要： A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least one auxiliary propulsion fan is configured to selectively receive a motive force from either or both of the at least two gas turbine engines through at least one shaft operatively coupled to the at least one auxiliary propulsion fan.
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公开(公告)号：US10830145B2
公开(公告)日：2020-11-10
申请号：US15956884
申请日：2018-04-19
摘要： A method of modulating cooling of gas turbine engine components includes the steps of identifying an input indicative of a usage rate for at least a first gas turbine engine component of a plurality of gas turbine engine components. A cooling system is operated for at least the first gas turbine engine component. The cooling system is moved between a higher cooling potential mode and a lower cooling potential mode based on the identified rate. A gas turbine engine is also disclosed.
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公开(公告)号：US20200347744A1
公开(公告)日：2020-11-05
申请号：US16805917
申请日：2020-03-02
摘要： A turbine engine according to an example of the present disclosure includes, among other things, a fan shaft, at least one tapered bearing mounted on the fan shaft, the fan shaft including at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing, a fan mounted for rotation on the at least one tapered bearing. An epicyclic gear train is coupled to drive the fan, the epicyclic gear train including a carrier supporting intermediate gears that mesh with a sun gear, and a ring gear surrounding and meshing with the intermediate gears, wherein the epicyclic gear train defines a gear reduction ratio of greater than or equal to 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train, the turbine section having a fan drive turbine that includes a pressure ratio that is greater than 5. The fan includes a pressure ratio that is less than 1.45, and the fan has a bypass ratio of greater than ten (10).
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8.发明授权公开(公告)号：US10808610B2
公开(公告)日：2020-10-20
申请号：US15925811
申请日：2018-03-20
摘要： An environmental control system includes a low pressure tap at a location on a first compressor section of a main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use.
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公开(公告)号：US10598047B2
公开(公告)日：2020-03-24
申请号：US15444942
申请日：2017-02-28
摘要： A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes an auxiliary electric motor control operable to control the core turning motor to drive rotation of the engine core using electric power while a full authority digital engine control that controls operation of the gas turbine engine is either depowered or in a power state that is less than a power level used by the full authority digital engine control in flight operation.
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公开(公告)号：US10584642B2
公开(公告)日：2020-03-10
申请号：US16027693
申请日：2018-07-05
摘要： A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan. A first compressor section is arranged in an axial flow relationship with the second compressor and the first and second turbines. A geared architecture operatively connects the first shaft and the fan. An inducer operative couples to the gear train.
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