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公开(公告)号：US20230012375A1
公开(公告)日：2023-01-12
申请号：US17371543
申请日：2021-07-09
摘要： A manufacturing method is provided that includes forming a radial flow turbine blade of a radial flow turbine rotor for a gas turbine engine. The radial flow turbine blade includes an internal cooling passage. At least a portion of the internal cooling passage has a passage thickness of less than 20 mils.
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公开(公告)号：US12110116B1
公开(公告)日：2024-10-08
申请号：US18217228
申请日：2023-06-30
发明人： Ryan A. Mitchell , Robert B. Fowler
IPC分类号： B64D13/06 , B64D13/08 , B64D27/10 , F02C3/13 , F02C6/08 , F02C6/18 , F02C7/08 , F02C9/42 , F02K3/12
CPC分类号： B64D13/06 , B64D13/08 , B64D27/10 , F02C3/13 , F02C6/08 , F02C6/18 , F02C7/08 , F02C9/42 , F02K3/12
摘要： A method of operation is provided during which a heating fluid is directed through a first passage into a combustor section to heat a component within the combustor section when an aircraft engine is in a first standby mode. The aircraft engine includes a flowpath, a compressor section, the combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath. The heating fluid is directed through a second passage into the exhaust section when the aircraft engine is in a second mode. The heating fluid is directed through the second passage bypasses the turbine section.
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