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1. 发明公开

EP3708792A1 GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 审中-公开
公开(公告)号：EP3708792A1
公开(公告)日：2020-09-16
申请号：EP20162850.0
申请日：2013-04-23
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , SCHWARZ, Frederick M. , KUPRATIS, Daniel Bernard , MERRY, Brian D. , ACKERMANN, William K.
IPC分类号： F01D25/16 , F02C7/06
摘要： A gas turbine engine (20) includes a very high speed low pressure turbine (46) such that a quantity defined by the exit area (401) of the low pressure turbine (46) multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine (54) is at a ratio between about 0.5 and about 1.5. The high pressure turbine (54) is supported by a bearing (142) positioned at a point where the first shaft (32) connects to a hub (500) carrying turbine rotors associated with the second turbine section (54).

2. 发明授权

EP3450723B1 PASSIVELY-DRIVEN BLEED SOURCE SWITCHING 有权
公开(公告)号：EP3450723B1
公开(公告)日：2020-04-15
申请号：EP18173670.3
申请日：2018-05-22
申请人： United Technologies Corporation
发明人： ORTIZ, Jonathan , ACKERMANN, William K. , FORCIER, Matthew P.
IPC分类号： F02C6/08 , F02C7/18 , F02C9/18

3. 发明授权

EP3228843B1 INTEGRATED AIRCRAFT ENVIRONMENTAL CONTROL AND BUFFER SYSTEM 有权转让
公开(公告)号：EP3228843B1
公开(公告)日：2019-11-13
申请号：EP17164172.3
申请日：2017-03-31
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , ACKERMANN, William K.
IPC分类号： F02C6/08 , B64D13/00 , B64D13/02 , B64D13/08 , F02C9/18

4. 发明授权

EP3228836B1 CONDITIONED LOW PRESSURE COMPRESSOR COMPARTMENT FOR GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3228836B1
公开(公告)日：2019-11-13
申请号：EP17163620.2
申请日：2017-03-29
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , SOBANSKI, Kurt J. , ACKERMANN, William K.
IPC分类号： F02K3/06 , F02C9/18 , F02C7/32 , F02C7/18 , F01D25/12

5. 发明公开

EP3467272A1 GEARED ARCHITECTURE FOR HIGH SPEED AND SMALL VOLUME FAN DRIVE TURBINE 审中-公开
公开(公告)号：EP3467272A1
公开(公告)日：2019-04-10
申请号：EP18191325.2
申请日：2014-02-17
申请人： United Technologies Corporation
发明人： McCUNE, Michael E. , HUSBAND, Jason , SCHWARZ, Frederick M. , KUPRATIS, Daniel Bernard , SUCIU, Gabriel L. , ACKERMANN, William K.
IPC分类号： F01D25/16 , F02C7/36
摘要： A gas turbine engine (20) includes a flex mount (78) for a fan drive gear system (60).

6. 发明公开

EP3406882A1 ACTIVE BLEED FLOW MODULATION 有权转让
公开(公告)号：EP3406882A1
公开(公告)日：2018-11-28
申请号：EP18173677.8
申请日：2018-05-22
申请人： United Technologies Corporation
发明人： ORTIZ, Jonathan , ACKERMANN, William K. , FORCIER, Matthew P.
IPC分类号： F02C6/08 , F02C7/18 , F02C9/18
CPC分类号： F02C7/18 , F01P2023/00 , F01P2025/04 , F01P2025/08 , F02C6/08 , F02C7/057 , F02C9/18 , F05D2270/301 , F05D2270/303 , F16K31/00
摘要： A bleed air cooling system (72) for a gas turbine engine includes a bleed port (58; 58a, 58b) located at an axial location of the gas turbine engine to divert a bleed airflow (66; 66a, 66b) from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct (60; 60a, 60b) in fluid communication with the bleed port (58; 58a, 58b) and configured to convey the bleed airflow (66; 66a, 66b) from the bleed port (58; 58a, 58b) to the bleed outlet. A modulating valve (74; 74a, 74b) is located at the bleed duct (60; 60a, 60b) and is movable between a fully open position and a fully closed position to regulate the bleed airflow (66; 66a, 66b) through the bleed duct (60; 60a, 60b) based on one or more operating conditions of the gas turbine engine.

7. 发明公开

EP3242000A1 FUNDAMENTAL GEAR SYSTEM ARCHITECTURE 审中-公开
标题翻译：基础齿轮系统结构
公开(公告)号：EP3242000A1
公开(公告)日：2017-11-08
申请号：EP17175088.8
申请日：2014-09-22
申请人： United Technologies Corporation
发明人： SHERIDAN, William G. , McCUNE, Michael E. , SCHWARZ, Frederick M. , KUPRATIS, Daniel Bernard , SUCIU, Gabriel L. , ACKERMANN, William K. , HUSBAND, Jason
IPC分类号： F01D25/16 , F02C7/36 , F01D21/04
CPC分类号： F02C7/36 , F01D21/045 , F01D25/16 , F05D2260/40311 , F05D2260/98 , Y02T50/671
摘要： A fan drive gear system for a gas turbine engine (20) includes a gear system (48) that provides a speed reduction between a fan drive turbine (46) and a fan (42) and a mount (76) flexibly supporting portions of the gear system (48). A lubrication system (98) supporting the fan drive gear system (48) provides lubricant to the gear system (48) and removes thermal energy produced by the gear system (48). The lubrication system (98) includes a capacity for removing energy equal to less than about 2% of energy input into the gear system (48).
摘要翻译：一种用于燃气涡轮发动机（20）的风扇驱动齿轮系统包括在风扇驱动涡轮（46）和风扇（42）之间提供减速的齿轮系统（48）以及柔性地支撑齿轮系统（48）。支撑风扇驱动齿轮系统（48）的润滑系统（98）向齿轮系统（48）提供润滑剂并去除由齿轮系统（48）产生的热能。润滑系统（98）包括用于去除等于输入到齿轮系统（48）中的能量的小于约2％的能量的能力。

8. 发明公开

EP3228844A1 INTEGRATED ENVIRONMENTAL CONTROL AND BUFFER AIR SYSTEM 有权转让
标题翻译：集成的环境控制和缓冲空气系统
公开(公告)号：EP3228844A1
公开(公告)日：2017-10-11
申请号：EP17164289.5
申请日：2017-03-31
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , ACKERMANN, William K. , HIPSKY, Harold W.
IPC分类号： F02C6/08 , B64D13/00 , B64D13/02 , B64D13/08 , F02C9/18
CPC分类号： F02C9/18 , B64D13/006 , B64D13/02 , B64D13/06 , B64D13/08 , B64D2013/0603 , F02C3/04 , F02C6/08 , F02C7/06 , F02C7/32 , F05D2220/323 , F05D2260/213 , F05D2260/606 , F05D2260/98
摘要： An environmental control system (62) for an aircraft includes a higher pressure tap (72) to be associated with a higher compression location and a lower pressure tap (74) to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure tap (74) communicates to a first passage leading to a downstream outlet, and has a second passage leading into a compressor section (80) of a turbocompressor (78). The higher pressure tap (72) leads into a turbine section (82) of the turbocompressor (78) such that air in the higher pressure tap (72) drives the turbine section (82) to in turn drive the compressor section (80) of the turbocompressor (78). A turbine outlet (86) receives airflow exhausted from the turbine section (82). A compressor outlet (84) receives airflow exhausted from the compressor section (80). A combined outlet (90) receives airflow from the turbine outlet (86) and the compressor outlet (84) intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet (112) communicates airflow to an engine buffer air system (66) and receives airflow supplied to the turbocompressor (78).
摘要翻译：用于飞机的环境控制系统（62）包括与较高压缩位置相关联的较高压力抽头（72）和与主压缩机部分中的较低压力位置相关联的较低压力抽头（74），所述较低压力位置与飞机发动机。低压龙头（74）与通向下游出口的第一通道连通，并具有通向涡轮压缩机（78）的压缩机部分（80）的第二通道。高压分接头72导入涡轮压缩机78的涡轮部分82中，使得高压分接头72中的空气驱动涡轮部分82继而驱动压缩机部分80的涡轮压缩机（78）。涡轮机出口（86）接收从涡轮机部段（82）排出的气流。压缩机出口（84）接收从压缩机部分（80）排出的气流。组合出口（90）接收来自涡轮机出口（86）和压缩机出口（84）的混合气流并使混合气流向下游通过的气流被输送到飞机。缓冲空气出口（112）将气流传送到发动机缓冲空气系统（66）并且接收供应到涡轮压缩机（78）的气流。

9. 发明公开

EP3133239A1 ASSEMBLY FOR ROTATIONAL EQUIPMENT AND CORRESPONDING AIRCRAFT PROPULSION SYSTEM 有权转让
标题翻译：佐治亚州流感病防治中心的ANORDNUNGFÜRROTIERENDE APPARATUR
公开(公告)号：EP3133239A1
公开(公告)日：2017-02-22
申请号：EP16184998.9
申请日：2016-08-19
申请人： United Technologies Corporation
发明人： ACKERMANN, William K. , CRAWLEY, Clifton J.Jr. , SCHWARZ, Frederick M.
IPC分类号： F01D5/06 , F01D5/08 , F01D11/02 , F16J15/44
CPC分类号： F04D29/083 , F01D5/06 , F01D5/082 , F01D11/02 , F04D29/324 , F04D29/542 , F04D29/545 , F04D29/582 , F05D2240/56 , F16J15/442 , F23R3/10 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： Assemblies are provided for rotational equipment. One of these assemblies includes a rotor disk structure 116, a stator structure 54 and a seal assembly 60. The rotor disk structure 116 includes a rotor disk 120 and a seal land 84 circumscribing the rotor disk 120. The stator structure 54 circumscribes the seal land 84. The seal assembly 60 is configured for sealing a gap between the stator structure 54 and the seal land 84, where the seal assembly 60 includes a noncontact seal 78. A corresponding aircraft propulsion system is also provided.
摘要翻译：为旋转设备提供组件。这些组件中的一个包括转子盘结构116，定子结构54和密封组件60.转子盘结构116包括转子盘120和限定转子盘120的密封接合面84.定子结构54限定密封接地密封组件60被构造用于密封定子结构54和密封接合区84之间的间隙，其中密封组件60包括非接触密封件78.还提供了相应的飞行器推进系统。

10. 发明公开

EP3054112A1 NOSE CONE ASSEMBLY AND METHOD OF CIRCULATING AIR IN A GAS TURBINE ENGINE 有权转让
标题翻译：在加拿大EINEM GASTURBINENMOTOR的NASENKEGELBAUGRUPPE UND VERFAHREN ZURLUFTFÜHRUNG
公开(公告)号：EP3054112A1
公开(公告)日：2016-08-10
申请号：EP16154872.2
申请日：2016-02-09
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , SNAPE, Nathan , BIFULCO, Anthony R. , ACKERMANN, William K. , ROSE, Becky E. , CHANDLER, Jesse M.
IPC分类号： F01D25/12 , F02C7/04 , F02C7/047 , F02C7/18 , F02C7/32 , F02C7/14
CPC分类号： F02K1/04 , F01D15/08 , F01D25/12 , F01D25/125 , F01D25/14 , F02C7/04 , F02C7/047 , F02C7/057 , F02C7/14 , F02C7/18 , F02C7/185 , F02C7/32 , F05D2220/32 , F05D2260/20 , F05D2260/213
摘要： A nose cone assembly (64) for a gas turbine engine (20) and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone (66) having an aperture (68) and communicating air to an interior space (70) of the nose cone and a discharge member (74) communicating the air out of the nose cone.
摘要翻译：公开了一种用于燃气涡轮发动机（20）的鼻锥组件（64）和在燃气涡轮发动机中循环空气的方法。鼻锥组件包括具有孔（68）并将空气连通到鼻锥的内部空间（70）的鼻锥（66）和将空气从鼻锥传出的排出构件（74）。

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