Invention Grant
- Patent Title: Auxiliary device for three air flow path gas turbine engine
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Application No.: US16521970Application Date: 2019-07-25
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Publication No.: US11261827B2Publication Date: 2022-03-01
- Inventor: Gary D. Roberge
- Applicant: Raytheon Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: Raytheon Technologies Corporation
- Current Assignee: Raytheon Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Carlson, Gaskey & Olds, P.C.
- Main IPC: F02K3/075
- IPC: F02K3/075 ; F02C9/18 ; F02K3/077 ; F02C3/13 ; F02C7/36 ; F02K3/10 ; F02K3/02 ; F02K3/00 ; F02C7/18 ; F02C7/141 ; F02K3/06 ; F02K1/08 ; F02K3/11
Abstract:
A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.
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