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1. 发明申请

US20220243682A1 THRUST EFFICIENT GAS TURBINE ENGINE 有权
公开(公告)号：US20220243682A1
公开(公告)日：2022-08-04
申请号：US17533607
申请日：2021-11-23
申请人： Raytheon Technologies Corporation
发明人： Jayant Sabnis
IPC分类号： F02K3/075 , F02K3/06 , F02C3/107 , F01D15/12 , F02K1/52 , B64D27/10 , F02C3/04 , F01D5/06 , F04D19/02 , F04D29/32 , F01D19/02
摘要： A disclosed gas turbine engine includes a gas generator section for generating a gas stream flow and a propulsor section for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The propulsor section includes a fan driven by a power turbine through a speed reduction device at a second rotational speed lower than a first rotational speed of the power turbine. An Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is between 0.05 and 0.13 during operation of the gas turbine engine.

2. 发明申请

US20210270207A1 EXHAUST NOZZLE WITH VANE SUPPORT STRUCTURE FOR A GAS TURBINE ENGINE 有权
公开(公告)号：US20210270207A1
公开(公告)日：2021-09-02
申请号：US16803535
申请日：2020-02-27
申请人： Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation
发明人： David L. Sutterfield , Jack D. Petty , Bryan H. Lerg , Andrew Sanderson
IPC分类号： F02K1/08 , B64D33/04 , F02K1/52
摘要： An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.

3. 发明申请

US20210190001A1 EXHAUST NOZZLE OF A GAS TURBINE ENGINE 有权
公开(公告)号：US20210190001A1
公开(公告)日：2021-06-24
申请号：US16719079
申请日：2019-12-18
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Predrag TODOROVIC
IPC分类号： F02K1/52
摘要： An exhaust nozzle of a gas turbine engine includes: a nozzle wall, a centerbody arranged in a flow channel, and two struts connecting the centerbody to the wall. One of the struts is connected to the wall by a coupling arrangement that includes two first brackets and a third bracket, the brackets being spaced in an axial direction and being connected either directly to the wall or to a sliding element that is arranged in a displaceable manner in the wall. The brackets each have a first, highest stiffness in a first direction and smaller stiffnesses in a second and third direction. The brackets are oriented such that with the two first brackets, the first direction is aligned with a circumferential direction of the nozzle and that with the third bracket, the first direction is aligned with the axial direction of the nozzle.

4. 发明授权

US10371092B2 Convergent divergent exit nozzle for a gas turbine engine 有权
公开(公告)号：US10371092B2
公开(公告)日：2019-08-06
申请号：US14817611
申请日：2015-08-04
申请人： United Technologies Corporation
发明人： Dmitriy B. Sidelkovskiy , Oleg Petrenko , Robert E. Malecki , Steven H. Zysman
IPC分类号： F02K1/78 , B64D29/00 , F02K1/40 , F02K1/52 , F02K1/00 , F02K1/82 , F02K1/36 , F02K3/077 , F02C3/04 , F02K3/06 , B64D29/02 , B64D29/04
摘要： A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.

5. 发明授权

US09624828B2 Thrust efficient turbofan engine 有权
公开(公告)号：US09624828B2
公开(公告)日：2017-04-18
申请号：US13871221
申请日：2013-04-26
申请人： United Technologies Corporation
发明人： Jayant Sabnis
IPC分类号： F02C3/04 , F02K1/52 , F02K3/06 , F02C3/08 , F02C6/02 , F02C7/36
CPC分类号： F02C3/04 , F02C3/08 , F02C6/02 , F02C7/36 , F02K1/52 , F02K3/06 , F05D2220/36
摘要： A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air. A power turbine converts the gas stream flow into shaft power. The power turbine rotates at a first rotational speed. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than about fifty (50) inches and an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is less than about 0.30 at a take-off condition.

6. 发明申请

US20120000179A1 REAR SECTION OF AIRCRAFT NACELLE AND NACELLE EQUIPPED WITH SUCH REAR SECTION 有权
标题翻译：具有这种后部装备的空中客车和后舱的后部分
公开(公告)号：US20120000179A1
公开(公告)日：2012-01-05
申请号：US12673288
申请日：2008-06-16
申请人： Eric Lecossais , Thierry Ledocte , Pascal Gerard Rouyer , Felix Carimali
发明人： Eric Lecossais , Thierry Ledocte , Pascal Gerard Rouyer , Felix Carimali
IPC分类号： F02K1/52
CPC分类号： B64D29/00
摘要： The invention relates to a rear section (11) of an aircraft nacelle, that comprises two halves (13a, 13b) defining: a central portion (C) for receiving a turbojet engine (7), a cool-air annular passage (31) provided around said central portion (C), and at least one six-hour cavity (15) provided under said central portion (C). The rear section is characterised in that it comprises at least one duct (29a, 29b) for the fluidic communication between said annular passage (31) and said six-hour cavity (15) for maintaining the temperature inside the six-hour cavity (15) within a relatively low range.
摘要翻译：本发明涉及飞机机舱的后部（11），其包括两个半部（13a，13b），其限定：用于容纳涡轮喷气发动机（7）的中央部分（C），冷空气环形通道（31）设置在所述中心部分（C）周围，以及设置在所述中心部分（C）下方的至少一个六小时空腔（15）。后部分的特征在于它包括用于在所述环形通道（31）和所述六小时空腔（15）之间流体连通的至少一个管道（29a，29b），用于保持六小时空腔内的温度（15 ）在相对较低的范围内。

7. 发明授权

US06971240B2 Methods and apparatus for exhausting gases from gas turbine engines 有权
标题翻译：从燃气涡轮发动机排出气体的方法和装置
公开(公告)号：US06971240B2
公开(公告)日：2005-12-06
申请号：US10812706
申请日：2004-03-30
申请人： Gary C. Wollenweber
发明人： Gary C. Wollenweber
IPC分类号： B64D29/08 , B64D33/04 , F02K1/46 , F02K1/52 , F02K1/82 , F02C7/20
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045
摘要： A method facilitates assembling a gas turbine engine. The method comprises mounting a core engine to a vehicle, coupling a fuselage radially outward and around the core engine, and coupling an exhaust nozzle to the core engine to channel exhaust gases discharged from the core engine. In addition, the method also comprises coupling an infrared suppression system in flow communication with the engine exhaust nozzle for channeling exhaust gases discharged from said exhaust nozzle to facilitate suppressing an exhaust infrared signature of the core engine during operation, wherein the infrared suppression system includes an access door and a flow channel that is coupled to the access door such that the flow channel is movable with the access door from a closed position to an open position.
摘要翻译：一种便于组装燃气涡轮发动机的方法。该方法包括将核心发动机安装到车辆上，将机身径向向外和围绕核心发动机联接，以及将排气喷嘴连接到核心发动机以引导从核心发动机排出的废气。此外，该方法还包括将与所述发动机排气喷嘴流体连通的红外线抑制系统联接，用于引导从所述排气喷嘴排出的废气，以便于在运行期间抑制所述核心发动机的废气红外特征，其中所述红外线抑制系统包括检修门和流动通道，其连接到检修门，使得流动通道可与检修门从关闭位置移动到打开位置。

8. 发明授权

US06969028B2 Scarf nozzle for a jet engine and method of using the same 有权
标题翻译：用于喷气发动机的围巾喷嘴及其使用方法
公开(公告)号：US06969028B2
公开(公告)日：2005-11-29
申请号：US10351159
申请日：2003-01-22
申请人： Roy Dun
发明人： Roy Dun
IPC分类号： B64D33/04 , F02K1/44 , F02K1/52 , B64D27/00
CPC分类号： B64C7/02 , B64D33/04 , F02K1/44 , F02K1/52 , Y02T50/671
摘要： A scarf nozzle for a jet engine supported within a nacelle. The scarf nozzle is at an aft end of the nacelle. The scarf nozzle includes a first trailing edge portion and a second trailing edge portion. The second trailing edge portion is disposed aft of the first trailing edge portion. The scarf nozzle is configured to allow the nacelle to be integrated closer to a wing without adversely affecting the pressure gradient between the nacelle and the wing. The scarf nozzle allows a portion of an exhaust plume exiting the aft end of the nacelle to interact more favorably with an airflow along one or more surfaces adjacent the nacelle, thus delaying the onset of adverse pressure gradients and the formation of shock waves between the nacelle and the adjacent surfaces and between the adjacent surfaces and the exhaust plume.
摘要翻译：用于支撑在机舱内的喷气发动机的围巾喷嘴。围巾喷嘴位于机舱的后端。围巾喷嘴包括第一后缘部分和第二后缘部分。第二后缘部分设置在第一后缘部分的后方。围巾喷嘴构造成允许机舱更靠近机翼集成，而不会不利地影响机舱和机翼之间的压力梯度。围巾喷嘴允许离开机舱的后端的一部分排气羽流与沿着机舱相邻的一个或多个表面的气流更有利地相互作用，从而延迟不利压力梯度的开始和在机舱之间形成冲击波和相邻表面之间以及相邻表面和排气羽流之间。

9. 发明授权

US4466587A Nacelle installation 失效
标题翻译：机舱安装
公开(公告)号：US4466587A
公开(公告)日：1984-08-21
申请号：US332893
申请日：1981-12-21
申请人： Donald J. Dusa , Conrad D. Wagenknecht
发明人： Donald J. Dusa , Conrad D. Wagenknecht
IPC分类号： B64D29/00 , B64C23/06 , B64D33/04 , F02K1/52 , B64C1/38
CPC分类号： B64C7/02 , B64C23/06 , B64D29/02 , B64D33/04 , F02K1/52 , F05D2270/173 , Y02T50/162 , Y02T50/671
摘要： Nacelle installation having devices for constraining hot core exhaust gas from flowing over the trailing portion of a highly swept pylon supporting a high bypass turbofan engine. The devices can comprise a pylon ejector, a core nozzle shroud or a plurality of vortex generators and are disposed generally in the region adjacent the intersection of the core nozzle exit of the engine and the pylon shelf portion of the pylon.
摘要翻译：机舱安装具有用于约束热核废气的装置，其流过支撑高旁路涡扇发动机的高度扫掠的塔架的尾部。该装置可以包括一个塔架喷射器，一个核心喷嘴罩或多个涡流发生器，并且大致设置在邻近发动机的核心喷嘴出口和塔架的塔架架部分的相交处的区域中。

10. 发明授权

US3409250A Movable fairing for an aircraftmounted nozzle 失效
标题翻译：用于飞机安装喷嘴的可移动整流罩
公开(公告)号：US3409250A
公开(公告)日：1968-11-05
申请号：US60476666
申请日：1966-12-27
申请人： GEN ELECTRIC
发明人： AMMER ROBERT C , BEAVERS ROBERT G , FERRARI BARTOLOMEO J , RABONE GEORGE R
IPC分类号： B64D33/04 , F02K1/12 , F02K1/52
CPC分类号： F02K1/1269 , B64D33/04 , F02K1/52

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