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公开(公告)号：US20170218789A1
公开(公告)日：2017-08-03
申请号：US15485512
申请日：2017-04-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
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公开(公告)号：US09695778B2
公开(公告)日：2017-07-04
申请号：US14184398
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: One embodiment includes a pivot thrust reverser comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator.
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公开(公告)号：US20170167386A1
公开(公告)日：2017-06-15
申请号：US14964984
申请日：2015-12-10
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F02C7/185 , F01D5/022 , F01D5/081 , F01D25/08 , F02C6/08 , F02C7/12 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2260/213 , F05D2260/40311 , Y02T50/676
Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.
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公开(公告)号：US09677475B2
公开(公告)日：2017-06-13
申请号：US14597442
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu
CPC classification number: F02C9/18 , F01D5/082 , F01D5/084 , F01D5/088 , F01D25/12 , F02C3/10 , F02C7/18 , F05D2250/322 , F05D2260/20 , Y02T50/676
Abstract: A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel. Compressor blades extend radially outward from the outer portion which provides an inner core flow path. A rotor spoke is configured to receive a first cooling flow and fluidly connect the outer portion to the cooling channel. The compressor rotor assembly has a coolant exit that is in fluid communication with the cooling channel. The compressor rotor assembly is configured to communicate the first cooling flow to the turbine rotor. A bleed source is configured to provide a second cooling flow. A combustor section includes an injector in fluid communication with the bleed source. The tangential onboard injector is configured to communicate the second cooling flow to the turbine rotor.
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公开(公告)号：US20170152756A1
公开(公告)日：2017-06-01
申请号：US14935673
申请日：2015-12-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , William G. Sheridan , Michael E. McCune , Gabriel L. Suciu
CPC classification number: F01D15/12 , F01D25/18 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/50 , F05D2260/40311 , F05D2260/98 , F16H1/28 , F16H57/0479 , F16H57/0486
Abstract: A gas turbine engine has a fan rotor, a turbine rotor driving the fan rotor, and an epicyclic gear reduction positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine is configured to drive the sun gear to, in turn, drive the ring gears to, in turn, drive the fan rotor.
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Patent Agency Ranking
公开(公告)号：US09650954B2
公开(公告)日：2017-05-16
申请号：US14597510
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Michael E. McCune , Jesse M. Chandler , Alan H. Epstein , Steven M. O'Flarity , Christopher J. Hanlon , William F. Schneider , Joseph B. Staubach , James A. Kenyon
IPC: F02C3/107 , B64D35/04 , F01D13/00 , F02K3/077 , F02C7/36 , F02C3/06 , F02C3/067 , F02C9/18 , B64D27/18
CPC classification number: F02C3/107 , B64D27/18 , B64D35/04 , F01D13/003 , F02C3/06 , F02C3/067 , F02C7/36 , F02C9/18 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312
Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.
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公开(公告)号：US20170122219A1
公开(公告)日：2017-05-04
申请号：US15411147
申请日：2017-01-20
Applicant: United Technologies Corporation
Inventor： Karl L. Hasel , Joseph B. Staubach , Brian D. Merry , Gabriel L. Suciu , Christopher M. Dye
IPC: F02C7/36 , F02C7/06 , F02K3/06 , F02C9/18 , F01D21/00 , F01D9/02 , F01D25/24 , F02C3/06 , F01D5/06
CPC classification number: F02C7/36 , F01D5/06 , F01D5/12 , F01D9/02 , F01D21/003 , F01D25/24 , F01D25/28 , F02C3/04 , F02C3/06 , F02C3/107 , F02C7/06 , F02C7/28 , F02C9/18 , F02K3/025 , F02K3/06 , F05D2220/32 , F05D2220/323 , F05D2240/12 , F05D2240/35 , F05D2240/55 , F05D2260/40 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than 8 at cruise power. A gear arrangement drives the fan section. A guide vane includes a forward attachment, the forward attachment positioned aft of a plumbing connection area. A compressor section includes both a first compressor and a second compressor. A lubrication system and a compressed air system are in fluid communication with the gear arrangement. A turbine section drives the gear arrangement, and includes a low pressure turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor, and greater than about 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor is greater than about 7.
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公开(公告)号：US20170122207A1
公开(公告)日：2017-05-04
申请号：US14932066
申请日：2015-11-04
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02C7/14 , B64C11/14 , F01D5/12 , F01D9/041 , F02C3/04 , F02C7/18 , F02K3/06 , F05D2220/32 , F05D2240/35 , F05D2260/213
Abstract: A gas turbine engine has a nose cone, a fan for delivering air into a bypass duct as bypass flow, and into a core engine to be delivered to a compressor. The nose cone includes a vent to receive air and deliver the air across a heat exchanger, which receives a fluid to be cooled. The air from the vents is delivered to an outlet downstream of the heat exchanger, such that a majority of the air being delivered to the outlet becomes part of the bypass flow.
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499.发明申请公开(公告)号：US20170114724A1
公开(公告)日：2017-04-27
申请号：US15399864
申请日：2017-01-06
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Daniel Bernard Kupratis , Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F02C7/36 , F01D5/06 , F01D25/162 , F02C3/06 , F02C3/107 , F02C7/06 , F02K3/06 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/40311
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. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.
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公开(公告)号：US09631578B2
公开(公告)日：2017-04-25
申请号：US14184313
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , T. David Bomzer
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: A pivot thrust reverser includes a first pivot door forming a first portion of a nacelle when stowed and second pivot door forming a second portion of the nacelle when stowed. The first pivot door and second pivot door each form a portion of a surface of a bypass duct when in a stowed position. In the deployed position the first pivot door and the second pivot door circumferentially surround a portion of an inner surface of a bypass duct such that when the pivot thrust reverser is deployed during engine operation a fan bypass stream is redirected while both a core stream and a nacelle ventilation stream flow in substantially the same manner as when the pivot thrust reverser is stowed.
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