Invention Grant
- Patent Title: Mitigation of effects of fan blade off in a gas turbine engine
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Application No.: US15933423Application Date: 2018-03-23
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Publication No.: US10677089B2Publication Date: 2020-06-09
- Inventor: Kieran P. Lucey , Stephen J. Bendall
- Applicant: ROLLS-ROYCE plc
- Applicant Address: GB London
- Assignee: Rolls-Royce PLC
- Current Assignee: Rolls-Royce PLC
- Current Assignee Address: GB London
- Agency: Simpson & Simpson, PLLC
- Priority: com.zzzhc.datahub.patent.etl.us.BibliographicData$PriorityClaim@402a5bf2
- Main IPC: F01D21/04
- IPC: F01D21/04 ; F01D5/02 ; F02C7/06 ; F01D21/08 ; F04D29/053 ; F04D29/044

Abstract:
A fan is mounted on a fan shaft which constitutes part of a mainline shaft assembly centered for rotation on an engine axis X-X of a gas turbine engine. When in operation, the fan rotates about the engine axis X-X. A stub-shaft is arranged radially outwardly and concentrically with the fan shaft and adjoins an upstream facing face of a bearing sleeve. A fan catcher arm extends from the stub-shaft through the bearing sleeve and joins a fan catcher ring arranged downstream of the bearing sleeve and having an upstream facing face arranged to abut against a downstream facing face of the bearing sleeve in the event of a fan blade-off. Immediately downstream of the fan catcher ring is formed a shaft end which is configured to couple with an axially adjacent end of a low pressure compressor shaft. Immediately downstream of the bearing sleeve is a shaft end configured to connect with a turbine shaft.
Public/Granted literature
- US20180283206A1 MITIGATION OF EFFECTS OF FAN BLADE OFF IN A GAS TURBINE ENGINE Public/Granted day:2018-10-04
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