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公开(公告)号：US20180106193A1
公开(公告)日：2018-04-19
申请号：US15292203
申请日：2016-10-13
Applicant: General Electric Company
CPC classification number: F02C3/04 , F01D17/162 , F02C3/10 , F02C3/145 , F05D2250/51 , F05D2250/80 , F05D2300/6033 , F23R3/54 , Y02T50/672
Abstract: A gas turbine engine includes a compressor section and turbine section. The gas turbine engine of the present disclosure is a relatively small gas turbine engine, configured to generate less than 2,000 horsepower during peak operations. The compressor section defines an overall compressor ratio of at least 15:1 in order to increase in overall efficiency of the gas turbine engine.
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公开(公告)号：US20210231052A1
公开(公告)日：2021-07-29
申请号：US17086580
申请日：2020-11-02
Applicant: General Electric Company
Inventor： Martin Miles D'Angelo , Mark Gregory Wotzak , Michael Macrorie
Abstract: A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the compressor, combustion section, turbine, and the exhaust section are in fluid communication. The inlet duct is positioned upstream of the compressor and defines an inlet portion of the air flowpath. The inlet duct is generally radially oriented. A variable inlet guide vane extends at least partially through the inlet duct.
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公开(公告)号：US20190061965A1
公开(公告)日：2019-02-28
申请号：US15682834
申请日：2017-08-22
Applicant: General Electric Company
Inventor： Kenneth Arthur Gould , Martin Miles D'Angelo , Daniel Waslo , Brian Lewis Devendorf , Mark Gregory Wotzak
Abstract: An apparatus and method for mounting a turbine engine to an aircraft can include an engine core for the turbine engine including a compressor section, a combustor section, and a turbine section in flow arrangement. At least one strut couples to the engine core about a single mount plane. A structural wall at least partially defining a mainstream flow path couples to the at least one strut and passes through the compressor section and the turbine section.
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公开(公告)号：US20180216527A1
公开(公告)日：2018-08-02
申请号：US15417937
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Martin Miles D'Angelo , Mark Gregory Wotzak , Michael Macrorie
CPC classification number: F02C7/042 , F01D25/30 , F02C3/04 , F02C3/145 , F02C9/20 , F04D29/542 , F04D29/545 , F04D29/563 , F05D2210/43 , F05D2220/3217 , F05D2250/90
Abstract: A turbine engine includes, in a serial flow relationship, an axially oriented compressor, a combustion section, a turbine section, and an exhaust section. An air flowpath extends from an inlet duct to the exhaust section such that the compressor, combustion section, turbine, and the exhaust section are in fluid communication. The inlet duct is positioned upstream of the compressor and defines an inlet portion of the air flowpath. The inlet duct is generally radially oriented. A variable inlet guide vane extends at least partially through the inlet duct.
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