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公开(公告)号：US20240229678A1
公开(公告)日：2024-07-11
申请号：US18613901
申请日：2024-03-22
发明人： Amit Arvind Kurvinkop , David Raju Yamarthi , David Allan Dranschak , Brian Christopher Kemp , Marc David Zinger , Parmeet Singh Chhabra , Roberto Karpik , Eliel Fresco Rodriguez
CPC分类号： F01D25/16 , F02C7/27 , F05D2220/32 , F05D2240/54 , F05D2260/85
摘要： An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support the drive shaft and the output shaft.
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公开(公告)号：US11655729B1
公开(公告)日：2023-05-23
申请号：US17680455
申请日：2022-02-25
CPC分类号： F01D19/00 , F02C7/27 , F05D2260/60 , F05D2260/85 , F05D2270/304 , F05D2270/52
摘要： The method can include generating a first duty cycle value for the PWM; monitoring a current value of a parameter; generating a duty cycle limit value for the PWM, including activating more than one duty cycle limit functions based on corresponding activation conditions, the corresponding activation conditions based on the current value of the parameter, each of the more than one duty cycle limit functions generating a corresponding duty cycle limit subvalue when the corresponding activation conditions are met, and setting the duty cycle limit value to a sum of the generated duty cycle limit subvalues; setting a second duty cycle value for the PWM, as the first duty cycle value or as the duty cycle limit if the first duty cycle value exceeds the duty cycle limit; and, applying the PWM at the second duty cycle value to the valve.
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公开(公告)号：US11454175B2
公开(公告)日：2022-09-27
申请号：US16654202
申请日：2019-10-16
发明人： Martin Richard Amari
摘要： A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.
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公开(公告)号：US20220056813A1
公开(公告)日：2022-02-24
申请号：US17358236
申请日：2021-06-25
发明人： Amit Arvind Kurvinkop , David Raju Yamarthi , David Allan Dranschak , Brian Christopher Kemp , Marc David Zinger , Parmeet Singh Chhabra , Roberto Karpik , Eliel Fresco Rodriguez
摘要： An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support one or more of the drive shaft, the carrier, or the output shaft.
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公开(公告)号：US11199137B2
公开(公告)日：2021-12-14
申请号：US16142317
申请日：2018-09-26
发明人： Alan H. Epstein
摘要： An engine system for an aircraft includes a first gas turbine engine, a first core turning system, a second gas turbine engine, and a second core turning system. The engine system also includes a controller operable to shutdown the first gas turbine engine responsive to determining that the aircraft has landed and operate in the second gas turbine engine in a taxi mode while using the first core turning system to cool the first gas turbine engine. The controller is further operable to shutdown the second gas turbine engine and disable the first core turning system based on a power-down condition, restart the first gas turbine engine and use the second core turning system to cool the second gas turbine engine based on a restart condition, and complete cooling of the second gas turbine prior to restarting the second gas turbine engine.
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公开(公告)号：US11174793B2
公开(公告)日：2021-11-16
申请号：US16135455
申请日：2018-09-19
摘要： A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first predefined threshold is met. The first predefined threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.
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公开(公告)号：US20210324801A1
公开(公告)日：2021-10-21
申请号：US16852856
申请日：2020-04-20
发明人： Cecilia Lam
摘要： Systems and methods to operate an engine in a bowed rotor mitigation mode. An engine starting system includes a starter coupled to the engine and with a compressor. A conduit system communicates a portion of the compressed air from the compressor to the starter. A load control valve controls compressed air from the compressor to the starter and to other loads. A starter air valve controls compressed air through the conduit system to the starter. At least one controller: receives a start signal from the engine; determines whether to initiate a bowed rotor mitigation of the engine; operates either the load control valve or the starter air valve to move to a predetermined static position; and operates the other of the load control valve or the starter air valve to achieve a target speed of the engine.
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公开(公告)号：US10975772B2
公开(公告)日：2021-04-13
申请号：US16269956
申请日：2019-02-07
发明人： Yiwei Jiang , James Vandung Nguyen , Edward W. Goy
摘要： A starter for a gas turbine engine includes a rotor shaft rotatable about an axis and includes an inner bore extending from an axial end of the rotor shaft with respect to the axis. A sun gear is on the rotor shaft. A lock nut is received against an axial end face of the sun gear and threadedly engaged with an outer diameter of the rotor shaft. A retainer is positioned to bias the nut against the axial end face and includes a projection portion threadedly engaged with the rotor shaft in the inner bore. A bolt through the projection portion is threadedly engaged with the rotor shaft.
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公开(公告)号：US20200239151A1
公开(公告)日：2020-07-30
申请号：US16829172
申请日：2020-03-25
摘要： A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine. A first controller is in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine.
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公开(公告)号：US10724443B2
公开(公告)日：2020-07-28
申请号：US15163279
申请日：2016-05-24
发明人： Robert Charles Hon , Thomas Charles Swager , Andrew Todd Lehmann , Michael Scott McCambridge , Thomas Earl Gillingham , Joseph Roger Broda , Kevin Richard Graziano , Amid Ansari , Kenneth Lee Kirchmayer , Tod Robert Steen , Daniel Roy Kiracofe
摘要： A method of operating a turbine engine that includes actuating a starter motor of the turbine engine such that a motoring speed of the turbine engine increases, and actuating a plurality of variable stator vanes of the turbine engine such that the plurality of variable stator vanes are at least partially open to control the motoring speed of the turbine engine.
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