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公开(公告)号：US20180045120A1
公开(公告)日：2018-02-15
申请号：US15791825
申请日：2017-10-24
Applicant: United Technologies Corporation
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US20180022459A1
公开(公告)日：2018-01-25
申请号：US14998001
申请日：2014-07-07
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu
CPC classification number: B64D13/06 , B64D27/26 , B64D2013/0603 , B64D2013/0618 , B64D2027/262 , F02C6/08 , F02C7/20 , F02K3/04
Abstract: A gas turbine engine includes a fan section delivering air into a compressor section. The compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. A pylon supports the engine. The pylon defines a lowermost surface and the higher pressure tap extends above a plane including the lowermost surface. The higher pressure tap includes a double wall tube above the plane for preventing leakage from impinging on a portion of the pylon. An environmental control system is also disclosed.
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公开(公告)号：US20170343011A1
公开(公告)日：2017-11-30
申请号：US15136416
申请日：2016-04-22
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Jeffrey D. Ponchak
CPC classification number: F04D29/544 , F01D5/141 , F01D9/041 , F02K3/06 , F04D29/083 , F05D2220/32 , F05D2240/121 , F05D2240/122 , Y02T50/673
Abstract: An improved stator assembly is disclosed. The stator assembly may comprise an exit guide vane, an OD ring, and an ID ring. The exit guide vane may couple at one end to the OD ring and at an opposite end to the ID ring. The exit guide vane may comprise a leading edge opposite of a trailing edge. The OD ring and the ID ring may couple to a diffuser assembly of a gas turbine engine. The stator assembly may further comprise an aft OD seal, a forward OD seal, an ID seal, and a diffuser assembly seal to reduce airflow leaks around the stator assembly.
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公开(公告)号：US20170335796A1
公开(公告)日：2017-11-23
申请号：US15652369
申请日：2017-07-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
IPC: F02K3/06 , F04D29/32 , F04D27/00 , F01D9/02 , F01D5/06 , F02C7/36 , F02C3/107 , F02C3/04 , F02C9/18 , F02K1/78
CPC classification number: F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US20170335690A1
公开(公告)日：2017-11-23
申请号：US15156382
申请日：2016-05-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John W. Golan , Frederick M. Schwarz
CPC classification number: F01D5/08 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2260/213 , F28D7/0025 , F28D7/1607 , F28D7/1684 , F28D2021/0026 , F28F1/045 , F28F1/10 , F28F13/08 , F28F2009/029
Abstract: A heat exchanger has a first plurality of fluid passages with an inlet manifold communicating into a core portion, and then an outlet manifold. A second plurality of fluid passages has an inlet manifold communicating into a core portion, and then into an outlet manifold and the core portions of both the first and second pluralities of fluid passages having smaller cross-sectional areas than cross-sectional areas of the inlet and outlet manifolds. A gas turbine engine and a method of forming a heat exchanger are also disclosed.
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Patent Agency Ranking
公开(公告)号：US20170335689A1
公开(公告)日：2017-11-23
申请号：US15156367
申请日：2016-05-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John W. Golan , Frederick M. Schwarz
IPC: F01D5/08 , F01D5/02 , F01D25/12 , F04D19/00 , F28F13/08 , F28F1/04 , B23P15/26 , F28D7/16 , F01D25/24 , F28D21/00
CPC classification number: F01D5/08 , B23P15/26 , F01D5/021 , F01D25/12 , F01D25/24 , F02C7/185 , F04D19/002 , F05D2220/32 , F05D2250/231 , F05D2260/213 , F28D7/1615 , F28D7/163 , F28D2021/0021 , F28D2021/0026 , F28F1/04 , F28F7/02 , F28F13/08 , F28F2210/08 , F28F2250/106 , F28F2255/14 , F28F2255/18 , Y02T50/675
Abstract: A heat exchanger has a first plurality of passages extending in a first direction and to receive a first fluid and a second plurality of passages extending in a second direction, and to receive a second fluid, and the first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of the first plurality of passages in different locations across the cross-sectional face of the heat exchanger. A gas turbine engine and a method of forming a heat exchanger are also disclosed.
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公开(公告)号：US09816442B2
公开(公告)日：2017-11-14
申请号：US14573003
申请日：2014-12-17
Applicant: United Technologies Corporation
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US20170298835A1
公开(公告)日：2017-10-19
申请号：US15488805
申请日：2017-04-17
Applicant: United Technologies Corporation
Inventor： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
CPC classification number: F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US20170298832A1
公开(公告)日：2017-10-19
申请号：US15292438
申请日：2016-10-13
Applicant: United Technologies Corporation
Inventor： Paul R. Adams , Shankar S. Magge , Joseph Brent Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
IPC: F02C7/36 , F01D11/12 , F01D25/24 , F02C3/04 , F02C9/18 , F02C7/20 , F04D19/02 , F01D5/06 , F02K3/06 , F02K3/075 , F02C3/107
CPC classification number: F02C7/36 , F01D5/06 , F01D11/122 , F01D25/24 , F02C3/04 , F02C3/107 , F02C7/20 , F02C9/18 , F02K3/06 , F02K3/075 , F04D19/02 , F05B2250/283 , F05D2220/32 , F05D2220/323 , F05D2240/35 , F05D2240/60 , F05D2260/40311
Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
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公开(公告)号：US20170298825A1
公开(公告)日：2017-10-19
申请号：US15097782
申请日：2016-04-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John W. Golan , Frederick M. Schwarz
Abstract: A gas turbine engine has a fan and a compressor section with a first lower pressure location and a second higher pressure location. A heat exchanger and a higher pressure tap from the second higher pressure location pass through the heat exchanger. Air in the higher pressure tap is cooled by air from a lower pressure tap from the first lower pressure location. A valve controls flow to the heat exchanger from the lower pressure tap, the valve being controlled to limit flow from the lower pressure tap under certain conditions.
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