Invention Grant
- Patent Title: Gas turbine engine mid turbine frame bearing support
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Application No.: US14818392Application Date: 2015-08-05
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Publication No.: US10753279B2Publication Date: 2020-08-25
- Inventor: Robert Russell Mayer , George J. Kramer , Paul W. Palmer
- Applicant: United 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: F02C1/00
- IPC: F02C1/00 ; F02C7/06 ; F02C3/045 ; F02C7/36 ; F02C7/20 ; F01D25/24 ; F01D25/16 ; F23R3/00 ; F23R3/60

Abstract:
A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.
Public/Granted literature
- US20150337732A1 GAS TURBINE ENGINE MID TURBINE FRAME BEARING SUPPORT Public/Granted day:2015-11-26
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