公开(公告)号：US12031450B2

公开(公告)日：2024-07-09

申请号：US17819641

申请日：2022-08-15

申请人： Garrett Transportation I Inc.

发明人： Haiying Sun ,  Xiongxiong Tang ,  Guangqing Zheng

IPC分类号： F01D25/24 ,  F01D9/04 ,  F01D11/00

CPC分类号： F01D25/246 ,  F01D9/041 ,  F01D11/003 ,  F05D2220/40 ,  F05D2230/64 ,  F05D2240/14 ,  F05D2250/12 ,  F05D2260/36

摘要： A turbocharger having a centrifugal compressor includes a vaned diffuser. The vaned diffuser is formed by a diffuser ring formed separately from the compressor housing and center housing. The diffuser ring is installed between the compressor and center housings such that a diffuser passage is defined between a surface of the compressor housing and a surface of the diffuser ring. Integral vanes on the diffuser ring extend only partially across the axial width of the diffuser passage. A rectangular-section seal ring is axially compressed between the compressor housing and the diffuser ring for sealing and axial locating of the diffuser ring. Radial locating of the diffuser ring is accomplished by an integral locating pin on the ring, which fits into a receptacle in the center housing.

公开(公告)号：US12006891B2

公开(公告)日：2024-06-11

申请号：US17679540

申请日：2022-02-24

申请人： Whisper Aero Inc.

发明人： Mark Douglass Moore ,  Ian Andreas Villa ,  Devon Jedamski

IPC分类号： B64D33/04 ,  F02K1/08 ,  F02K1/12

CPC分类号： F02K1/1207 ,  F05D2220/323 ,  F05D2240/128 ,  F05D2250/12 ,  F05D2250/141 ,  F05D2260/57

摘要： A propulsor system comprising a propulsor and an exhaust area control mechanism are described. The exhaust area control mechanism is connected to an outlet of the propulsor and is configured to vary the area through which air exits the propulsor system.

公开(公告)号：US11719112B2

公开(公告)日：2023-08-08

申请号：US17814021

申请日：2022-07-21

申请人： ROLLS-ROYCE plc

发明人： Michael Yeandel

IPC分类号： F02C7/32 ,  F01D9/06

CPC分类号： F01D9/06 ,  F02C7/32 ,  F05D2250/11 ,  F05D2250/12 ,  F05D2260/60

摘要： A tube gallery for a gas turbine engine includes a body. The body includes an external surface. The body also includes a plurality of channels defined in the body. Each channel includes an inlet disposed on the external surface, an outlet spaced apart from the inlet and disposed on the external surface, and a passage extending between and fluidly communicating the inlet to the outlet. The passage of each channel has a non-circular cross-sectional shape. The non-circular cross-sectional shape has a first maximum dimension along a first direction and a second maximum dimension along a second direction orthogonal to the first direction. The first maximum dimension is greater than the second maximum dimension by a factor of at least 1.2.

公开(公告)号：US20230175458A1

公开(公告)日：2023-06-08

申请号：US17542861

申请日：2021-12-06

申请人： Rohr, Inc.

发明人： Andrew J. Strutt

IPC分类号： F02K1/82 ,  F02K1/34 ,  G10K11/168

CPC分类号： F02K1/827 ,  B64D33/06 ,  G10K11/168 ,  F05D2260/96 ,  F05D2250/12 ,  F05D2250/132 ,  F05D2250/11 ,  F05D2250/283

摘要： An aircraft propulsion system apparatus includes a first skin, a second skin, an intermediate layer between the first skin and the second skin, a first cellular core and a second cellular core. The first cellular core is connected to the first skin and the intermediate layer. The first cellular core includes a plurality of first core chambers, where a first of the first core chambers is fluidly coupled with one or more first perforations in the first skin and one or more first perforations in the intermediate layer. The second cellular core is connected to the intermediate layer and the second skin. The second cellular core includes a plurality of second core chambers and a plurality of corrugations, where a first of the second core chambers is fluidly coupled with the first of the first core chambers through the one or more first perforations in the intermediate layer.

公开(公告)号：US09976744B2

公开(公告)日：2018-05-22

申请号：US14063065

申请日：2013-10-25

申请人： Ansaldo Energia Switzerland AG

发明人： John Philip Wood ,  Andrea Ciani ,  Andre Theuer ,  Douglas Anthony Pennell ,  Ewald Freitag

IPC分类号： F23R3/20 ,  F23R3/16 ,  F02C6/00 ,  F23R3/34 ,  F23R3/12 ,  F02C6/02 ,  F23R3/18

CPC分类号： F23R3/20 ,  F02C6/003 ,  F02C6/02 ,  F05D2250/12 ,  F05D2250/13 ,  F23R3/12 ,  F23R3/16 ,  F23R3/18 ,  F23R3/34 ,  F23R3/346 ,  F23R2900/03341

摘要： A reheat burner arrangement including a center body, an annular duct with a cross-section area, an intermediate fuel injection plane located along the center body and being actively connected to the cross section area of the annular duct, wherein the center body is located upstream of a combustion chamber, wherein the structure of the reheat burner arrangement is defined by various parameters and the structure of the reheat burner arrangement is defined by various dependencies.

公开(公告)号：US20180066527A1

公开(公告)日：2018-03-08

申请号：US15547709

申请日：2015-12-08

申请人： Siemens Aktiengesellschaft

发明人： Kai Kadau ,  Jose Antonio Pascual-Gutierrez ,  Atin Sharma

IPC分类号： F01D5/28 ,  F01D11/12 ,  F01D5/18 ,  C23C28/00 ,  C23C4/18 ,  C23C4/073 ,  C23C4/02

CPC分类号： F01D5/288 ,  C23C4/02 ,  C23C4/073 ,  C23C4/18 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/186 ,  F01D11/122 ,  F05D2230/30 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/12 ,  F05D2250/132 ,  F05D2250/294 ,  F05D2260/22141

摘要： Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have vertically aligned engineered surface features (ESFs) (632, 634) and furcated engineered groove features (EGFs) (642, 652). A planform pattern of EGFs (642, 652) is cut into the outer surface of the component's thermal barrier coating (TBC). The EGF pattern includes a planform pattern of overlying vertices (644) respectively in vertical alignment with an underlying corresponding ESF (632, 634). At least three respective groove segments (642, 652, 642) within the EGF pattern (640) converge at each respective vertex (644) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σA) is furcated (σB, σC) at each successive vertex juncture.

公开(公告)号：US20170234141A1

公开(公告)日：2017-08-17

申请号：US15044775

申请日：2016-02-16

申请人： General Electric Company

发明人： Ronald Scott Bunker ,  Robert David Briggs

IPC分类号： F01D5/18 ,  F01D5/14

CPC分类号： F01D5/187 ,  F05D2240/303 ,  F05D2250/12 ,  F05D2250/14 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

摘要： An airfoil for a turbine engine having first and second radially extending cooling chambers separated by a radially extending rib in which rows of crossover holes pass through the rib and fluidly coupling the first and second chambers.

公开(公告)号：US20170058700A1

公开(公告)日：2017-03-02

申请号：US15227599

申请日：2016-08-03

申请人： Rolls-Royce North American Technologies, Inc.

发明人： Tab M. Heffernan ,  Kenneth M. Pesyna

IPC分类号： F01D25/30 ,  F01D25/04 ,  F01D9/04

CPC分类号： F01D25/30 ,  F01D9/04 ,  F01D25/04 ,  F02K1/48 ,  F05D2220/32 ,  F05D2230/237 ,  F05D2230/642 ,  F05D2250/12 ,  F05D2250/141 ,  F05D2250/16 ,  F05D2260/941 ,  F05D2260/96

摘要： A gas turbine engine exhaust component is disclosed herein. The gas turbine engine exhaust component includes an annular mixer that extends around a central axis and is formed to include inner lobes that define radially-outwardly opening channels and outer lobes that define radially-inwardly opening channels. A constraint band is added to connect the outer lobes and reduce vibration, deflections, and stresses.

摘要翻译： 本文公开了一种燃气涡轮发动机排气部件。 燃气涡轮发动机排气部件包括围绕中心轴线延伸并且形成为包括限定径向向外的开口通道的内凸角和限定径向向内开口通道的外凸角的环形混合器。 添加约束条带以连接外裂片并减少振动，偏转和应力。

公开(公告)号：US20170044905A1

公开(公告)日：2017-02-16

申请号：US15235568

申请日：2016-08-12

申请人： Doosan Heavy Industries & Construction Co., Ltd.

发明人： Jong Hoon Park

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/288 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2240/30 ,  F05D2240/81 ,  F05D2250/12 ,  F05D2250/22 ,  F05D2260/202

摘要： A gas turbine blade has a trench part of a film cooling unit for cooling a blade part that is formed at a tip of a film cooling hole part. As a result, cooling efficiency of the blade can be improved since the blade part is sufficiently cooled even during introduction of a large amount of cooling air, durability of the blade can be increased by inhibiting the blade from being damaged due to hot gas since the trench part is formed to have a minimum width, and efficiency of a gas turbine can be increased by an improvement in film efficiency.

摘要翻译： 燃气轮机叶片具有用于冷却形成在薄膜冷却孔部分的尖端处的叶片部分的薄膜冷却单元的沟槽部分。 结果，即使在大量冷却空气的引入期间叶片部分被充分冷却，也可以提高叶片的冷却效率，通过抑制由于热气体而导致的叶片的损坏，能够提高叶片的耐久性 沟槽部形成为具有最小宽度，并且可以通过提高膜效率来提高燃气轮机的效率。

公开(公告)号：US20160312795A1

公开(公告)日：2016-10-27

申请号：US15105212

申请日：2014-11-24

申请人： GENERAL ELECTRIC COMPANY

发明人： David William CRALL

IPC分类号： F04D29/52 ,  B64D33/02 ,  B64D29/00 ,  F04D29/02 ,  F04D29/32

CPC分类号： F04D29/526 ,  B64D29/00 ,  B64D33/02 ,  F01D11/127 ,  F01D21/045 ,  F01D25/24 ,  F04D29/023 ,  F04D29/325 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/132 ,  F05D2250/18 ,  F05D2300/603 ,  Y02T50/672

摘要： A ribbed composite shell includes an annular grid of relatively thick crack arresting ribs embedded in a relatively thin annular shell and relatively thin panels in thin annular shell between arresting ribs wherein each of panels are completely surrounded by a set of relatively thick adjoining ones of ribs. A shell forward flange may extend radially inwardly from thin annular shell. Arresting ribs may include radially stacked layers of strips between radially stacked annular layers of shell. Annular grid may include a rectangular grid pattern, a diamond grid pattern, or a hexagonal grid pattern. A nacelle inlet may have the ribbed composite shell within one or both of radially spaced apart composite inner and outer skins of an inner barrel. Nacelle inlet may be part of attached to a fan casing and axially disposed forward of fan blades circumscribed by the casing. The inlet may be on an engine nacelle.

摘要翻译： 肋状复合壳体包括嵌入相对薄的环形壳体中的相对较厚的防裂肋的环形格栅，以及在阻挡肋之间的薄环形壳体中的相对薄的板，其中每个板被一组相对较厚的相邻的肋部包围。 外壳向前法兰可从薄的环形外壳径向向内延伸。 阻挡肋可以包括在径向层叠的壳的环形层之间的径向堆叠的条带。 环形网格可以包括矩形网格图案，菱形网格图案或六边形网格图案。 机舱入口可以在内筒的径向间隔开的复合内外表面的一个或两个内具有肋状复合壳。 机舱入口可以是附接到风扇壳体并且轴向地设置在由壳体限定的风扇叶片的前面的一部分。 入口可以在发动机机舱上。