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公开(公告)号：US10794292B2
公开(公告)日：2020-10-06
申请号：US15420221
申请日：2017-01-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis , Frederick M. Schwarz
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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公开(公告)号：US10794291B2
公开(公告)日：2020-10-06
申请号：US15015198
申请日：2016-02-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan situated at an inlet of a bypass passage, and a core engine configured to drive the fan. The core engine includes a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section. The fan has a fan diameter, Dfan, and the high pressure compressor section has a compressor diameter, Dcomp. The fan diameter Dfan and the compressor diameter Dcomp have an interdependence represented by a scalable ratio Dfan/Dcomp that is greater than about 4.5.
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公开(公告)号：US20200277918A1
公开(公告)日：2020-09-03
申请号：US16736013
申请日：2020-01-07
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft and a plurality of planetary gears. A first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. An annular channel axially is aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1. A low fan pressure ratio is less than 1.45 across the fan blade alone.
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公开(公告)号：US10605104B2
公开(公告)日：2020-03-31
申请号：US14765217
申请日：2014-02-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Simon Pickford
Abstract: A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger. The second lubricant circuit is fluidly coupled with the first lubricant circuit, and the second turbine engine component includes a bearing. The shaft is supported by the bearing, and connected to one of the engine stages.
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公开(公告)号：US20200095929A1
公开(公告)日：2020-03-26
申请号：US16676788
申请日：2019-11-07
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Karl L. Hasel , Brian D. Merry
Abstract: A ratio of an outer diameter of a fan hub at a leading edge of the blades to an outer tip diameter of the blades at the leading edge is greater than or equal to about 0.24 and less than or equal to about 0.38. The fan tip diameter is greater than or equal to about 84 inches (213.36 centimeters) and a fan tip speed is less than or equal to about 1050 ft/second (320.04 meters/second). The fan drive turbine has between three and six stages.
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Patent Agency Ranking
公开(公告)号：US10570824B2
公开(公告)日：2020-02-25
申请号：US14949273
申请日：2015-11-23
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Michael E. McCune
Abstract: A system is provided for a turbine engine. This turbine engine system includes a rotating assembly, a bearing and a lubrication system. The bearing is configured with the rotating assembly. The lubrication system is configured to lubricate the bearing. The lubrication system includes a lubricant pump and a lubricant reservoir. The lubricant pump is mechanically coupled with and driven by the rotating assembly. The lubricant pump is configured with the lubricant reservoir so as to be at least partially submersed in lubricant contained within the lubricant reservoir.
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公开(公告)号：US10563582B2
公开(公告)日：2020-02-18
申请号：US15000618
申请日：2016-01-19
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
IPC: F02C7/18 , F28D1/053 , F28F13/06 , F28D1/04 , F02C7/14 , F28D21/00 , F28D1/02 , F02C3/04 , F02C7/36 , F02C9/18
Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.
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公开(公告)号：US20200032667A1
公开(公告)日：2020-01-30
申请号：US16453405
申请日：2019-06-26
Applicant: United Technologies Corporation
Inventor： Jeffrey D. Ponchak , Frederick M. Schwarz , David L. Motto
Abstract: A seal assembly for a gas turbine engine includes first and second split-ring seals. The first split-ring seal includes circumferentially separated first and second ends, laterally separated first and second edges, a first sealing lobe adjacent the first edge, and a first integral clip portion adjacent the second edge. The first sealing lobe has a curved surface extending laterally outward from the first edge. The second split-ring seal is slidably received and nested in the first seal. The second split-ring seal includes circumferentially separated third and fourth ends and laterally separated third and fourth edges.
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公开(公告)号：US20200011247A1
公开(公告)日：2020-01-09
申请号：US16027787
申请日：2018-07-05
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Jorn Axel Glahn
Abstract: A gas turbine engine includes a first tap connected to a compressor section to deliver air at a first pressure. A heat exchanger is downstream of the first tap. A cooling air valve selectively blocks flow of cooling air across the heat exchanger. A cooling compressor is downstream of the heat exchanger and pressurizes the air from the first tap to a greater second pressure. A shut off valve selectively stops flow of the air between the heat exchanger and the cooling compressor. A controller controls the cooling air valve, the shut off valve, and the cooling compressor such that the flow of the air is stopped between the heat exchanger and the cooling compressor only after the controller has stopped the cooling compressor. A monitoring system communicates with the controller and includes a pressure sensor and a temperature sensor downstream of the cooling compressor.
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公开(公告)号：US20190323431A1
公开(公告)日：2019-10-24
申请号：US15956853
申请日：2018-04-19
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Taryn Narrow
Abstract: A gas turbine engine includes a plurality of rotatable components housed within a compressor section and a turbine section. A tap is connected to a location upstream of a downstream most location in the compressor section. The tap is connected to a heat exchanger. Downstream of the heat exchanger is a shut off valve and downstream of the shut off valve is a cooling compressor. The cooling compressor is connected to deliver cooling air through a chamber, and then to at least one of the plurality of rotatable components. The chamber is provided with at least one check valve configured to selectively allow flow directly from a more downstream location in the compressor section than the location upstream. The flow from the more downstream location has a higher pressure than a flow from the location upstream. There is a system for stopping operation of the cooling compressor. There is a control for closing the shut off valve. The cooling compressor is configured to compress air to a greater pressure than the higher pressure, such that when the cooling compressor is providing air, the at least one check valve is configured to maintain a closed position, but when said cooling compressor is not providing compressed air, the at least one check valve is configured to allow said higher pressure flow into said chamber. A method is also disclosed.
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