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公开(公告)号：US09777595B2
公开(公告)日：2017-10-03
申请号：US14704631
申请日：2015-05-05
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Gabriel L. Suciu
CPC classification number: F01D25/12 , B64C11/14 , F01D25/18 , F02C7/04 , F02C7/06 , F02C7/14 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2260/213 , F05D2260/40311 , F05D2260/98 , Y02T50/676
Abstract: An oil cooling system is provided. The system may comprise an oil inlet, a manifold fluidly coupled to the oil inlet, and a support strut comprising internal tubing fluidly coupled to the manifold. A heat exchanger may be fluidly coupled to the internal tubing of the support strut. A nose cone may be disposed forward of the heat exchanger and configured to rotate about an axis. The heat exchanger may be radially inward from a portion of the nose cone. A gas turbine engine is also provided. The gas turbine engine may comprise an epicyclic gear system and fan mechanically coupled to the epicyclic gear system. The fan may be configured to rotate about an axis. A nose cone may be coupled to the fan and configured to rotate about the axis. A heat exchanger may be aft of the fan and in fluid communication with the epicyclic gear system.
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公开(公告)号：US20170276011A1
公开(公告)日：2017-09-28
申请号：US15079392
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jesse M. Chandler , Gabriel L. Suciu , Joseph Stack
CPC classification number: F01D17/162 , F01D9/04 , F01D9/042 , F01D17/12 , F01D17/14 , F01D17/16 , F01D25/34 , F16H19/005 , F16H49/001 , Y02T50/671 , Y02T50/673
Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.
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公开(公告)号：US20170276010A1
公开(公告)日：2017-09-28
申请号：US15606522
申请日：2017-05-26
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 according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades supported by a fan shaft support defining a fan shaft support lateral and transverse stiffness. A gear system connected to the fan shaft including a ring gear defining a ring gear lateral and transverse stiffness, a gear mesh defining a gear mesh lateral and transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral and transverse stiffness is less than 12% of a respective one of the gear mesh lateral and transverse stiffness. A flexible support supports the gear system and defines a flexible support lateral and transverse stiffness. At least one of the flexible support lateral and transverse stiffness is less than 11% of a respective one of the fan shaft support lateral and transverse stiffness.
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公开(公告)号：US20170254219A1
公开(公告)日：2017-09-07
申请号：US15062442
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry
Abstract: A gas turbine engine comprises an engine having a compressor section, and a turbine section. A firewall and accessory pumps are mounted on a downstream side of the firewall. The accessory pumps are driven by electric motors mounted on the firewall on an upstream side of the firewall.
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155.发明申请公开(公告)号：US20170234159A1
公开(公告)日：2017-08-17
申请号：US15478671
申请日：2017-04-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
CPC classification number: F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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Patent Agency Ranking
公开(公告)号：US09726112B2
公开(公告)日：2017-08-08
申请号：US14190144
申请日：2014-02-26
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
IPC: F02K3/06
CPC classification number: F02K3/06 , F05D2210/40 , F05D2250/314 , Y02T50/671
Abstract: A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.
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公开(公告)号：US20170218844A1
公开(公告)日：2017-08-03
申请号：US15011762
申请日：2016-02-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul R. Hanrahan , Gabriel L. Suciu
CPC classification number: F02C7/185 , F02C3/04 , F02C6/08 , F02C7/12 , F02C7/32 , F02C9/22 , F05D2220/32 , F05D2260/213 , F05D2260/232 , Y02T50/676
Abstract: A gas turbine engine has a main compressor section. A turbine section has a variable vane positioned upstream of a rotor blade, and the variable vane is provided with an actuator operable to control an orientation of the variable vane. A tap line taps air from the compressor section, and passes the tapped air through a cooling compressor. The cooling compressor is a fixed flow compressor. Air downstream of the cooling compressor is delivered into the turbine section.
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公开(公告)号：US20170167384A1
公开(公告)日：2017-06-15
申请号：US14967518
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
CPC classification number: F02C7/18 , F01D5/08 , F02C3/04 , F02C7/143 , F02C7/185 , F02C9/18 , F02K3/06 , F04D27/0215 , F04D29/582 , F05D2220/32 , F05D2220/3219 , F05D2240/24 , F05D2260/205 , F05D2260/211 , F05D2260/213 , Y02T50/676
Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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公开(公告)号：US20170122220A1
公开(公告)日：2017-05-04
申请号：US15411173
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 , F02C9/18 , F01D25/24 , F01D5/06 , F01D9/02 , F01D21/00 , F02C3/06 , F02K3/06
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, 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 or equal to 10 at cruise power, and a low fan pressure ratio of less than 1.45 measured across a fan blade alone. A gear arrangement drives the fan section. A compressor section includes both a low pressure compressor and a high pressure compressor. A guide vane includes a forward attachment, the forward attachment positioned aft of a plumbing connection area. A turbine section drives the gear arrangement, and may have a low pressure turbine with a low pressure turbine pressure ratio greater than 5:1, and a two stage high pressure turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor and a pressure ratio across the high pressure compressor, and greater than 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the high pressure compressor is greater than 7.
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公开(公告)号：US09611048B2
公开(公告)日：2017-04-04
申请号：US14187038
申请日：2014-02-21
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: B64D29/06 , F01D9/02 , F01D25/24 , F01D25/28 , F05D2220/32 , F05D2230/70 , F05D2230/72 , F05D2230/80 , F05D2240/121 , F05D2240/122 , F05D2240/128 , F05D2240/1281 , F05D2240/14 , F05D2240/55 , F05D2240/91 , F05D2250/192 , F05D2250/292 , F05D2250/294 , F05D2250/34 , F05D2250/75 , F05D2260/96 , Y10T29/49721
Abstract: A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extends in the aft direction from the first annular portion. A second annular portion is positioned aft of the first portion and coupled to the rail. The second portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion in the closed position, thereby providing access to the engine core. A mating axial groove and rib connection is located between the first annular portion and the second annular portion.
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