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1. 发明公开

EP4372219A1 ZONED LINER EXHAUST WITH BURIED N-CORE 审中-公开
公开(公告)号：EP4372219A1
公开(公告)日：2024-05-22
申请号：EP23208894.8
申请日：2023-11-09
申请人： Rohr, Inc.
发明人： KOROLY, Christopher C. , ALONSO-MIRALLES, Jose S.
IPC分类号： F02C7/24 , F02K1/34 , F02K1/44 , F02K1/82
CPC分类号： F02K1/827 , F05D2260/9620130101 , B64D33/06 , F02C7/24 , F02K1/44
摘要： A center plug (206) for attenuating noise in a gas turbine engine (122) includes an inner skin (330), a forward bulkhead (346), and aft bulkhead (334), and a noise attenuation panel (452). The inner skin has a substantially cylindrical shape and extending along an axial centerline. The forward bulkhead is disposed proximate a forward end of the inner skin. The forward bulkhead is connected to and extends radially outward from the inner skin. The aft bulkhead is disposed proximate an aft end of the inner skin. The aft bulkhead is connected to and extending radially outward from the inner skin. The noise attenuation panel is positioned intermediate the inner skin and partially divides a region bounded by the inner skin, the forward bulkhead and the aft bulkhead into.

2. 发明授权

EP2354493B1 Ejector/mixer nozzle for noise reduction 有权
标题翻译：用于降噪的喷射器/混合器喷嘴
公开(公告)号：EP2354493B1
公开(公告)日：2018-04-11
申请号：EP10196293.4
申请日：2010-12-21
申请人： General Electric Company
发明人： Zhang, Hua , Ball, David Wesley
IPC分类号： F02C7/045 , F01D25/30 , F02K1/34 , F02K1/36 , F02K1/38 , F02K1/44 , F02K1/46 , F01N1/14 , F02C7/04 , F02C7/08
CPC分类号： F02C7/045 , F01D25/30 , F01N1/14 , F02C7/04 , F02C7/08 , F02K1/34 , F02K1/36 , F02K1/386 , F02K1/44 , F02K1/46
摘要： An inlet bleed heat system in a gas turbine includes a compressor discharge extraction manifold (12) that extracts compressor discharge air, an inlet bleed heat manifold (18) receiving the compressor discharge air, and a plurality of acoustic dispersion nozzles (26) disposed at an output end of the inlet bleed heat manifold that reduce a velocity of the compressor discharge air in the inlet bleed heat manifold. Noise is generated from the shearing action between the surrounding atmosphere and air jets from orifices. When the air jet velocity is slowed using, for example, a multi-stage ejector/mixer, noise can be abated.

3. 发明公开

EP2730501A3 Rotational annular airscrew with integrated acoustic arrester 有权
标题翻译：带集成式消声器的旋转环形螺旋桨
公开(公告)号：EP2730501A3
公开(公告)日：2017-11-15
申请号：EP13192605.7
申请日：2013-11-12
申请人： The Boeing Company
发明人： Moore, Matthew D. , Boren, Kelly L.
IPC分类号： B64C11/00 , F02K3/072 , B64C11/18 , F01D1/24 , F02K1/44 , F02K5/00 , F04D29/32 , B63H5/10
CPC分类号： F02K5/00 , B64C11/001 , B64C11/18 , F01D1/24 , F01D5/03 , F01D5/225 , F02K1/44 , F02K1/827 , F02K3/062 , F02K3/072 , F04D29/326 , F05D2260/96 , Y02T50/672 , Y02T50/673 , Y10T137/0536
摘要： A propulsion system and methods are presented. A substantially tubular structure (102) comprises a central axis (104) through a longitudinal geometric center, and a first fan (108) rotates around the central axis, and comprises a first fan hub (110) and first fan blades (112). The fan hub (108) is rotationally coupled to the substantially tubular structure (102), and the first fan blades (112) are coupled to the first fan hub (110) and increase in chord length with increasing distance from the first fan hub (108). A second fan (118) is rotationally coupled to the substantially tubular structure (102) and rotates around the central axis and contra-rotates relative to the first fan (108). Second fan blades (118) are coupled to the second fan hub (120), and a nacelle (124) circumscribing the first fan (108) and the second fan (118) is coupled to and rotates with the first fan (108).
摘要翻译：介绍了一种推进系统和方法。大致管状结构（102）包括穿过纵向几何中心的中心轴线（104），并且第一风扇（108）围绕中心轴线旋转，并且包括第一风扇轮毂（110）和第一风扇叶片（112）。风扇轮毂108旋转地联接到大致管状结构102，并且第一风扇叶片112联接到第一风扇轮毂110并且随着距离第一风扇轮毂110的距离增加而增加弦长。 108）。第二风扇（118）可旋转地联接到大致管状结构（102）并围绕中心轴线旋转并且相对于第一风扇（108）反转。第二风扇叶片118联接到第二风扇轮毂120，外接第一风扇108和第二风扇118的机舱124联接到第一风扇108并与第一风扇108一起旋转。

4. 发明公开

EP2980393A1 GAS TURBINE ENGINE EJECTOR 有权
标题翻译： EJEKTOR EINER FLUGGASTURBINE
公开(公告)号：EP2980393A1
公开(公告)日：2016-02-03
申请号：EP15179131.6
申请日：2015-07-30
申请人： Pratt & Whitney Canada Corp.
发明人： DI POLA, Franco , LEFEBVRE, Guy , L'ESPERANCE, Patrick , EMARD-PARENT, Gabriel
IPC分类号： F02K1/04 , F02K1/36 , F02K1/38 , F02K1/48 , F02K1/44 , F02K1/34
CPC分类号： F02K1/386 , F02C3/10 , F02K1/34 , F02K1/48 , F05D2220/324 , F05D2250/232 , F05D2250/61 , F05D2260/601
摘要： An ejector (200) comprises a primary nozzle (201) having an annular wall (234) forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine (10). The annular wall (234) has a downstream end (37) defining a plurality of circumferentially distributed lobes (236). The ejector (200) further comprises a secondary nozzle (203) having an annular wall (234) disposed about the primary nozzle (201), the primary nozzle (201) and the secondary nozzle (203) defining a secondary flow passage (207) therebetween for channeling a secondary flow. The secondary nozzle (203) defines a mixing zone (209) downstream of an exit of the primary nozzle (201). A flow guide ring (205) is mounted to the primary nozzle lobes (236). The ring (205) has an aerodynamic surface extending from a leading edge (205a) to a trailing edge (205b) respectively disposed upstream and downstream of the exit of the primary nozzle (201). The aerodynamic surface of the ring (205) is oriented to guide the high velocity primary flow into the mixing zone (209).
摘要翻译：喷射器（200）包括具有形成燃气涡轮发动机（10）的主流路的排气部分的外边界的一部分的环形壁（234）的主喷嘴（201）。环形壁（234）具有限定多个周向分布的叶片（236）的下游端（37）。喷射器（200）还包括具有围绕主喷嘴（201）设置的环形壁（234）的辅助喷嘴（203），主喷嘴（201）和辅助喷嘴（203）限定二次流动通道（207）用于引导二次流。辅助喷嘴（203）限定了主喷嘴（201）的出口下游的混合区（209）。流动导向环（205）安装到主喷嘴孔（236）上。环（205）具有从前缘（205a）延伸到分别设置在主喷嘴（201）的出口的上游和下游的后缘（205b）的空气动力学表面。环（205）的空气动力学表面被定向成将高速一次流引导到混合区（209）中。

5. 发明公开

EP2762714A2 Exhaust cone 审中-公开
标题翻译： Auslasskonus
公开(公告)号：EP2762714A2
公开(公告)日：2014-08-06
申请号：EP13197681.3
申请日：2013-12-17
申请人： Rolls-Royce plc
发明人： Morvant, Romuald
IPC分类号： F02K1/82 , F02K1/34 , F02K1/44
CPC分类号： F02C7/24 , F02K1/34 , F02K1/44 , F02K1/827
摘要： A gas turbine engine exhaust cone (40) comprising one or more acoustic absorption chambers (48), each chamber (48) comprising two side walls (50) and an acoustic attenuation wall (62). The side walls (50) define the circumferential extent of the chamber (48). The acoustic attenuation wall (62) has one or more acoustic attenuators (64) and is positioned circumferentially intermediate the side walls (50). The side walls (50) extend axially along the exhaust cone (40) at least one of them with a circumferential progression. The acoustic attenuation wall (62) extends axially along the exhaust cone (40) with or without a circumferential progression.
摘要翻译：包括一个或多个声吸收室（48）的燃气涡轮发动机排气锥（40），每个室（48）包括两个侧壁（50）和声衰减壁（62）。侧壁（50）限定了腔室（48）的圆周范围。声衰减壁（62）具有一个或多个声衰减器（64），并且位于侧壁（50）的周向周向。侧壁（50）沿着排气锥体（40）轴向延伸至少其中一个具有圆周渐进。声衰减壁（62）沿着排气锥（40）轴向延伸，带有或不具有圆周的前进。

6. 发明公开

EP1397586A1 EXHAUST FLOW GUIDE FOR JET NOISE REDUCTION 有权
标题翻译：排气流量GUIDE减轻空气喷射声
公开(公告)号：EP1397586A1
公开(公告)日：2004-03-17
申请号：EP02727068.5
申请日：2002-04-10
申请人： Pratt & Whitney Canada Corp.
发明人： TSE, Man-Chun
IPC分类号： F02K1/28 , F02K1/34 , F02K1/36 , F02K1/38 , F02K1/46 , F02K1/48 , F02K1/50 , F02K1/82 , F02K1/44
CPC分类号： B64D33/06 , F02K1/34 , F02K1/38 , F02K1/386 , F02K1/44 , F02K1/46 , F02K1/48 , F02K1/50 , F05D2250/61 , Y02T50/671
摘要： A gas turbine engine includes an exhaust flow guide attached to the engine exhaust end. The exhaust flow guide is made of a piece of sheet metal curved about the central longitudinal axis of the engine to form a partial portion of a nozzle having curved leading and trailing edges, and side edges. The exhaust flow guide asymmetrically affects the downstream jet noise contribution volume of the exhaust gases discharged from the engine exhaust end to change the jet noise directivity and reduce its power level. The exhaust flow guide can further include additional features such as perforations, corrugated surfaces, reinforcing strips and irregularly shaped trailing edges to further improve the mixing of exhaust gas flow with surrounding fluid flow to further reduce the downstream jet noise contribution volume, thereby resulting in jet noise reduction. The exhaust flow guide according to the present invention also improves attenuation of engine noise generated in the engine and emitted from the engine exhaust end. The present invention provides a jet noise reduction device which is simple and economical to manufacture and maintain, and is applicable to both short and long cowl nacelle gas turbine engines.

7. 发明公开

EP1262666A3 Air inlet and outlet silencer structures for turbine 有权
标题翻译： Lufteinlass- und auslassstrukturenfürTurbinen
公开(公告)号：EP1262666A3
公开(公告)日：2004-01-21
申请号：EP01126835.6
申请日：2001-11-10
申请人： M & I Heat Transfer Products Ltd.
发明人： Han, Ming Hui (Peter)
IPC分类号： F04D29/66 , F02K1/44 , F02C7/045 , F01D25/30 , F01N1/24
CPC分类号： F04D29/664 , F01D25/30 , F02C7/045 , F05D2250/50 , F05D2260/96
摘要： Both air duct inlet silencers and air duct outlet silencers (18,20) for use with a stationary gas turbine (12) are disclosed. The inlet silencer (18) comprises a vertically extending duct structure (34) having an upper section (36) with a plurality of vertically extending sides and a top cover. Air inlet openings (48) are formed in the vertically extending sides and an air outlet (51) is formed at the bottom end for connection to the air intake housing of the turbine. An elongate, central airflow defining member (60) is substantially cylindrical for a major portion of its length and extends downwardly from the top cover (40) and past the air inlets (48). This member has a perforated sheet metal exterior and contains sound attenuating material. Airflow passages extend from the inlet openings (48) towards the outlet (51) with each defined by at least one interior wall. Each passageway bends substantially downwardly so that the bottom section extends vertically. The outlet silencer (20) includes first and second series of splitters (176,178) with each series forming smaller air passageways (180,182).
摘要翻译：公开了用于固定式燃气轮机（12）的空气管道入口消音器和风道出口消音器（18,20）。入口消音器（18）包括具有上部（36）的垂直延伸的管道结构（34），其具有多个垂直延伸的侧面和顶盖。空气入口开口（48）形成在垂直延伸的侧面，并且在底端处形成空气出口（51），用于连接到涡轮机的进气口。细长的中央气流限定构件（60）在其长度的大部分上基本上是圆柱形的并且从顶盖（40）向下延伸并且经过空气入口（48）。该构件具有穿孔的金属板外部并且包含声音衰减材料。气流通道从入口开口（48）朝向出口（51）延伸，每个由至少一个内壁限定。每个通道基本上向下弯曲，使得底部部分垂直延伸。出口消音器（20）包括第一和第二系列分离器（176,178），每个系列形成较小的空气通道（180,182）。

8. 发明公开

EP1359308A1 Outlet silencer and heat recovery structures for gas turbine 有权
标题翻译： AuslassschalldämpferfürGasturbinen
公开(公告)号：EP1359308A1
公开(公告)日：2003-11-05
申请号：EP02014082.8
申请日：2002-07-01
申请人： M & I Heat Transfer Products Ltd.
发明人： Han, Ming Hui (Peter) , Yazici, Muammer
IPC分类号： F02K1/40 , F02K1/44 , F01N1/08 , F01N1/16 , F02C6/00
CPC分类号： F28F9/0263 , F01D25/30 , F01N1/24 , F01N5/02 , F01N2310/02 , F02C7/08 , F22B1/1815
摘要： A sound attenuating duct unit (40) suitable for connection to an outlet of a gas turbine (10) and an improved heat recovery apparatus for use with such a turbine are disclosed. The former unit includes a duct housing (42) having exterior sides, an air inlet (46) at one end and first and second air outlets (80, 64). Interior walls define a main airflow passageway extending from the air inlet to both of the outlets. Sound absorbing material (101) is arranged between these walls and the exterior sides. Sound attenuating members (120) are mounted in the passageway and a diverter damper (96) is mounted in the housing and is able to direct air flow to either one of the air outlets. The sound attenuating members (120) are mounted between the diverter damper and the air inlet (46). The heat recovery apparatus includes a series of aerodynamic diffusers (175, 200) mounted in a housing adjacent an air flow inlet connectable to the gas turbine (10).
摘要翻译：公开了适于连接到燃气轮机（10）的出口的声音衰减管道单元（40）和用于这种涡轮机的改进的热回收设备。前一单元包括具有外侧的导管壳体（42），一端的空气入口（46）和第一和第二空气出口（80,64）。内壁限定从空气入口延伸到两个出口的主要气流通道。吸声材料（101）布置在这些壁和外侧之间。声音衰减构件（120）安装在通道中，并且转向阻尼器（96）安装在壳体中并且能够将空气流引导到任一个空气出口。声音衰减构件（120）安装在转向挡板和进气口（46）之间。热回收装置包括一系列空气动力学扩散器（175,200），其安装在邻近可连接到燃气轮机（10）的空气流入口的壳体中。

9. 发明授权

EP3290897B1 BANC D'ESSAI DE TURBOMACHINE AVEC CONTRÔLE ACTIF DU BRUIT 有权
公开(公告)号：EP3290897B1
公开(公告)日：2020-02-12
申请号：EP17188927.2
申请日：2017-09-01
申请人： Safran Aero Boosters SA
发明人： MEYS, Benoît , LACROIX, Alain
IPC分类号： G01M15/02 , F01D21/00 , F02C7/045 , G10K11/178 , B64F5/60 , G01M15/14 , F02K1/44 , F02K1/82

10. 发明授权

EP2730501B1 Rotational annular airscrew with integrated acoustic arrester 有权
公开(公告)号：EP2730501B1
公开(公告)日：2019-04-24
申请号：EP13192605.7
申请日：2013-11-12
申请人： The Boeing Company
发明人： Moore, Matthew D. , Boren, Kelly L.
IPC分类号： B64C11/00 , F02K3/072 , B64C11/18 , F01D1/24 , F02K1/44 , F02K5/00 , F04D29/32 , B63H5/10

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