Invention Grant
- Patent Title: Reconfigurable exhaust nozzle for a gas turbine engine
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Application No.: US16836080Application Date: 2020-03-31
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Publication No.: US11408368B2Publication Date: 2022-08-09
- Inventor: David L. Sutterfield , Todd S. Taylor , Jack D. Petty , Andrew Sanderson , Bryan H. Lerg
- Applicant: Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation
- Applicant Address: US IN Indianapolis; US IN Indianapolis
- Assignee: Rolls-Royce North American Technologies Inc.,Rolls-Royce Corporation
- Current Assignee: Rolls-Royce North American Technologies Inc.,Rolls-Royce Corporation
- Current Assignee Address: US IN Indianapolis; US IN Indianapolis
- Agency: Barnes & Thornburg LLP
- Main IPC: F02K1/08
- IPC: F02K1/08 ; F02K1/34 ; F02K1/70 ; F02K1/04 ; F02K1/62 ; F02K1/76
Abstract:
A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.
Public/Granted literature
- US20210301760A1 RECONFIGURABLE EXHAUST NOZZLE FOR A GAS TURBINE ENGINE Public/Granted day:2021-09-30
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