Invention Grant
- Patent Title: Reverse flow gas turbine engine with offset RGB
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Application No.: US15407401Application Date: 2017-01-17
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Publication No.: US11035293B2Publication Date: 2021-06-15
- Inventor: Jean Dubreuil
- Applicant: PRATT & WHITNEY CANADA CORP.
- Applicant Address: CA Longueuil
- Assignee: PRATT & WHITNEY CANADA CORP.
- Current Assignee: PRATT & WHITNEY CANADA CORP.
- Current Assignee Address: CA Longueuil
- Agency: Norton Rose Fulbright Canada LLP
- Main IPC: F02C3/107
- IPC: F02C3/107 ; F02C6/20 ; F02C3/14 ; F02C7/32 ; F02C7/36

Abstract:
A gas turbine engine has an engine case housing a low pressure compressor drivingly connected to a low pressure turbine by a low pressure compressor shaft extending along an engine axis. The low pressure turbine is disposed forward of the low pressure compressor. A low pressure turbine shaft is drivingly connected to the low pressure turbine and extends forwardly of the low pressure turbine. A reduction gear box (RGB) is drivingly connected to the low pressure turbine shaft. The RGB is offset from the engine axis to free an access to low pressure compressor shaft connection. The offset positioning of the RGB allows to provide an access port in an axially forwardly facing surface of the engine case to access the low pressure compressor shaft and more particularly a connection thereof to the low pressure turbine.
Public/Granted literature
- US20180073429A1 REVERSE FLOW GAS TURBINE ENGINE WITH OFFSET RGB Public/Granted day:2018-03-15
Information query
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