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公开(公告)号：US20180023509A1
公开(公告)日：2018-01-25
申请号：US15218138
申请日：2016-07-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry
CPC classification number: F02K1/70 , F02K1/72 , F02K3/06 , F02K3/062 , F05D2220/323 , F05D2230/72
Abstract: A gas turbine engine has a core engine and a fan. A pivoting D-door structure includes a pivoting inner D-door portion and an outer D-door portion, which is axially moveable relative to the inner D-door portion between a stowed and thrust reverse position. A fan case surrounds the fan. Cascades are axially moveable along with the outer D-door portion between a stowed and a thrust reverse position. Structure supporting the cascades is mounted on the fan case.
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公开(公告)号：US09869183B2
公开(公告)日：2018-01-16
申请号：US14799994
申请日：2015-07-15
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Wesley K. Lord
CPC classification number: F01D5/082 , F01D5/084 , F01D5/085 , F01D5/288 , Y02T50/672 , Y02T50/676
Abstract: A rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotor disk rotatable about an axis and a gas path wall coupled to and radially outward of the rotor disk. The gas path wall bounds a radially inward portion of a gas path. A plurality of rotor spokes are radially intermediate the rotor disk and the gas path wall. The plurality of rotor spokes is circumferentially spaced to define a plurality of cooling channels intermediate the rotor disk and the gas path wall. A thermal barrier coating is disposed on a surface of at least one of the plurality of cooling channels. A method of cooling a rotor assembly is also disclosed.
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公开(公告)号：US09850819B2
公开(公告)日：2017-12-26
申请号：US14695504
申请日：2015-04-24
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
CPC classification number: F02C7/185 , F01D25/12 , F02C3/13 , F02C7/143 , F05D2210/44 , F05D2220/3212 , F05D2220/3218 , F05D2260/211 , F05D2260/213 , F05D2260/606 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US20170363098A1
公开(公告)日：2017-12-21
申请号：US15186729
申请日：2016-06-20
Applicant: United Technologies Corporation
Inventor： Stephen H. Taylor , Charles E. Lents , Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler
CPC classification number: F04D27/009 , F01D5/02 , F01D15/08 , F01D15/12 , F01D17/145 , F02C6/08 , F02C7/32 , F04D25/02 , F04D27/004 , F04D27/023 , F04D29/321 , F05D2220/32 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes a main engine compressor section. A booster compressor changing a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor operates at airflow conditions greater than a demand by the pneumatic system. A speed change system driving the booster compressor at speeds corresponding to a demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.
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公开(公告)号：US09845159B2
公开(公告)日：2017-12-19
申请号：US14190175
申请日：2014-02-26
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
CPC classification number: B64D29/06 , B64D27/20 , F01D13/003 , F02K1/52 , F02K1/54 , F02K1/60 , F02K1/64 , F05D2250/314
Abstract: A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.
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Patent Agency Ranking
公开(公告)号：US09797311B2
公开(公告)日：2017-10-24
申请号：US14729800
申请日：2015-06-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Allan R. Penda , Brian D. Merry , Christopher M. Dye , Nathan Snape
CPC classification number: F02C7/185 , F02C7/08 , F02C7/14 , F02C7/18 , Y02T50/671
Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.
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公开(公告)号：US09752510B2
公开(公告)日：2017-09-05
申请号：US15000077
申请日：2016-01-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Alan H. Epstein , Wesley K. Lord , Michael E. McCune , Brian D. Merry
CPC classification number: F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
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公开(公告)号：US09574520B2
公开(公告)日：2017-02-21
申请号：US14190178
申请日：2014-02-26
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry
CPC classification number: F02K1/70 , B64D29/06 , B64D33/04 , F05D2250/314 , Y02T50/671
Abstract: A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.
Abstract translation: 用于安装在飞行器的机翼下方的燃气涡轮发动机具有在第一轴线上旋转的推进器和包括压缩机部分，燃烧器部分和涡轮部分的发动机核心，其中涡轮机部分更靠近推进器， 压缩机部分。 发动机机芯与空气动力学连接，并具有第二轴。 机舱位于推进器和发动机内核周围。 机舱附着在飞机的机翼上。 机舱的下游端具有至少一个枢转门，其具有致动机构，以使门在收起位置和水平展开位置之间枢转，门中阻止流动以提供逆流。
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公开(公告)号：US20160237909A1
公开(公告)日：2016-08-18
申请号：US14837009
申请日：2015-08-27
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02C7/185 , F02C3/04 , F02C6/08 , F02C7/277 , F02C7/32 , F02K3/025 , F02K3/065 , F02K3/075 , F05D2260/213 , Y02T50/671 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor is connected to be driven with at least one rotor in the main compressor section. A source of pressurized air is selectively sent to the cooling compressor to drive a rotor of the cooling compressor to rotate, and to in turn drive the at least one rotor of the main compressor section at start-up of the gas turbine engine. An intercooling system is also disclosed.
Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 冷却压缩机被连接以在主压缩机部分中用至少一个转子驱动。 加压空气源被选择性地送到冷却压缩机以驱动冷却压缩机的转子旋转，并且在燃气涡轮发动机起动时又驱动主压缩机段的至少一个转子。 还公开了一种中间冷却系统。
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公开(公告)号：US20160237908A1
公开(公告)日：2016-08-18
申请号：US14804534
申请日：2015-07-21
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler
IPC: F02C7/18
CPC classification number: F02C6/08 , F02C7/143 , F02C7/185 , F02C7/32 , F05D2260/213 , Y02T50/671 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passing the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger also receives air to be delivered to an aircraft cabin. An intercooling system for a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，使抽头的空气通过热交换器，然后通过冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 热交换器还接收要传送到飞机机舱的空气。 还公开了一种用于燃气涡轮发动机的中间冷却系统。
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