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公开(公告)号：US20210381439A1
公开(公告)日：2021-12-09
申请号：US17406652
申请日：2021-08-19
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Andre M. Ajami , Sami Chukrallah , Richard M. Marshall , Ryan W. Hunter
Abstract: 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 threshold is met. The first 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：US11965458B2
公开(公告)日：2024-04-23
申请号：US17535128
申请日：2021-11-24
Applicant: Raytheon Technologies Corporation
Inventor： Andre M. Ajami , Ryan W. Hunter , Javier A. Cue
CPC classification number: F02C5/02 , F02C3/04 , F02C3/13 , F02C7/32 , F05D2220/34 , F05D2240/35 , F05D2260/213 , F05D2260/232 , F05D2260/99
Abstract: An engine system is provided that includes a compressor section, a combustor section, a turbine section, a flowpath and a flow regulator. The combustor section includes a combustion chamber. The flowpath extends sequentially through the compressor section, the combustor section and the turbine section. The flow regulator is configured to open the flowpath between the compressor section and the combustion chamber during a first mode of operation. The flow regulator is configured to at least substantially close the flowpath between the compressor section and the combustion chamber during a second mode of operation.
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公开(公告)号：US20230160339A1
公开(公告)日：2023-05-25
申请号：US17535128
申请日：2021-11-24
Applicant: Raytheon Technologies Corporation
Inventor： Andre M. Ajami , Ryan W. Hunter , Javier A. Cue
CPC classification number: F02C5/02 , F02C7/32 , F05D2240/35 , F05D2220/34 , F05D2260/213 , F05D2260/232 , F05D2260/99
Abstract: An engine system is provided that includes a compressor section, a combustor section, a turbine section, a flowpath and a flow regulator. The combustor section includes a combustion chamber. The flowpath extends sequentially through the compressor section, the combustor section and the turbine section. The flow regulator is configured to open the flowpath between the compressor section and the combustion chamber during a first mode of operation. The flow regulator is configured to at least substantially close the flowpath between the compressor section and the combustion chamber during a second mode of operation.
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公开(公告)号：US11506128B2
公开(公告)日：2022-11-22
申请号：US17406652
申请日：2021-08-19
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Andre M. Ajami , Sami Chukrallah , Richard M. Marshall , Ryan W. Hunter
Abstract: 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 threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.
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