公开(公告)号：US08950171B2

公开(公告)日：2015-02-10

申请号：US13089450

申请日：2011-04-19

Applicant: Gabriel Suciu ,  Brian Merry ,  Michael E. McCune

Inventor： Gabriel Suciu ,  Brian Merry ,  Michael E. McCune

IPC: B63H11/00 ,  F02C3/073 ,  F02C3/107 ,  F02C3/08 ,  F02K3/068 ,  F02C7/36 ,  F04D25/04 ,  F16H48/10

CPC classification number: F02C3/08 ,  F02C3/073 ,  F02C3/107 ,  F02C7/36 ,  F02K3/068 ,  F04D25/045 ,  F05D2260/40311 ,  F16H48/10

Abstract: A tip turbine engine provides an axial compressor rotor that is counter-rotated relative to a fan. A planetary gearset couples rotation of a fan to an axial compressor rotor, such that the axial compressor rotor is driven by rotation of the fan in a rotational direction opposite that of the fan. By counter-rotating the axial compressor rotor, a final stage of compressor vanes between the final stage of compressor blades and inlets to the hollow fan blades of the fan are eliminated. As a result, the length of the axial compressor and the overall length of the tip turbine engine are decreased.

Abstract translation: 尖端涡轮发动机提供相对于风扇反向旋转的轴向压缩机转子。 行星齿轮组将风扇的旋转耦合到轴向压缩机转子，使得轴向压缩机转子通过风扇沿与风扇相反的旋转方向的旋转来驱动。 通过逆向旋转轴向压缩机转子，消除了在压缩机叶片的最后阶段和到风扇的中空风扇叶片的入口之间的压缩机叶片的最后阶段。 结果，轴流压缩机的长度和末端涡轮发动机的总长度减小。

公开(公告)号：US20140165582A1

公开(公告)日：2014-06-19

申请号：US13716247

申请日：2012-12-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Victor Pascu ,  Nipulkumar G. Shah

IPC: F02C7/18 ,  F02C9/16

CPC classification number: F02C9/16 ,  F02C3/08 ,  F02C3/14 ,  F02C7/06 ,  F05D2260/20 ,  Y02T50/671 ,  Y02T50/675

Abstract: An embodiment of the present invention is a gas turbine engine including a compressor, a turbine, an annular combustor, an exhaust duct, a first engine shaft bearing, and a second engine shaft bearing. The turbine has an axial flow direction toward the compressor. The combustor has an axial flow direction away from the compressor. The exhaust duct is disposed between the compressor and the combustor. The first engine shaft bearing is disposed on an axial side of the compressor opposite the turbine. The second engine shaft bearing is disposed on an axial side of the turbine opposite the compressor.

Abstract translation: 本发明的一个实施例是一种燃气涡轮发动机，其包括压缩机，涡轮机，环形燃烧器，排气管，第一发动机轴轴承和第二发动机轴轴承。 涡轮机具有朝向压缩机的轴向流动方向。 燃烧器具有远离压缩机的轴向流动方向。 排气管设置在压缩机和燃烧器之间。 第一发动机轴轴承设置在与涡轮机相对的压缩机的轴向侧。 第二发动机轴轴承设置在与压缩机相对的涡轮的轴向侧。

公开(公告)号：US20130202406A1

公开(公告)日：2013-08-08

申请号：US13799406

申请日：2013-03-13

Applicant: United Technologies Corporation

Inventor： Federico Papa ,  Thomas G. Phillips ,  Kathleen R. Phillips ,  Ethan K. Stearns ,  Justin W. Heiss

IPC: F01D25/12

CPC classification number: F02C7/12 ,  F01D25/12 ,  F02C3/08 ,  F02C7/06 ,  F02C7/08 ,  F02C7/14 ,  F02C7/224 ,  F02C7/232 ,  F02C9/00 ,  F02C9/48 ,  F05D2220/32 ,  F05D2260/213 ,  G05B15/02 ,  G05D7/06 ,  Y02T50/675

Abstract: A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的热管理系统尤其包括热交换器和阀，其控制通过热交换器A连通的第一流体的量第一传感器感测到 第二流体的第一特征，其通过热交换器连通以与第一流体交换热量，第二传感器感测第二流体的第二特性。 阀的定位基于第一特征和第二特性中的至少一个。

公开(公告)号：US20130067933A1

公开(公告)日：2013-03-21

申请号：US13604579

申请日：2012-09-05

Applicant: Bjoern Veith ,  Carlos Simon-Delgado ,  Daniel Seng ,  Andreas Haubitz

Inventor： Bjoern Veith ,  Carlos Simon-Delgado ,  Daniel Seng ,  Andreas Haubitz

IPC: F02C3/04

CPC classification number: F02C3/04 ,  F01D5/081 ,  F01D5/082 ,  F01D25/12 ,  F02C3/08 ,  F02C7/18

Abstract: A gas turbine is provided and includes a compressor, which via an air intake inducts and compresses air; a combustion chamber, in which a fuel is combusted using the compressed air, producing a hot gas; and a turbine, equipped with turbine blades, in which the hot gas is expanded, performing work. A first device is provided in order to cool turbine blades with compressed cooling air. The first device includes at least one separate compressor stage which produces compressed cooling air independently of the compressor.

Abstract translation: 提供一种燃气轮机，并包括通过进气口进气并压缩空气的压缩机; 燃烧室，其中使用压缩空气燃烧燃料，产生热气体; 以及配备有涡轮叶片的涡轮机，其中热气体膨胀，进行工作。 提供第一装置以便用压缩的冷却空气冷却涡轮机叶片。 第一装置包括至少一个单独的压缩机级，其独立于压缩机产生压缩的冷却空气。

公开(公告)号：US08235648B2

公开(公告)日：2012-08-07

申请号：US12239264

申请日：2008-09-26

Applicant: Andre LeBlanc

Inventor： Andre LeBlanc

IPC: F02C6/08 ,  F01D1/06 ,  F04D27/02

CPC classification number: F04D29/444 ,  F02C3/08 ,  F04D29/681 ,  F05D2240/12 ,  F05D2250/52 ,  F05D2270/101

Abstract: A diffuser for a centrifugal impeller assembly of a gas turbine engine includes a diffuser case having a plurality of vanes extending therein defining a plurality of circumferentially distributed angled passages in communication with an inlet space. Each vane includes a bleed port defined in a suction surface thereof, in proximity of the leading edge. The diffuser case includes a passive fluid communication defined at least partially through each one of the vanes between each bleed port and the inlet space upstream of the leading edge, such that air bled through the bleed ports is recirculated upstream of the leading edges to the inlet space to increase a surge margin of the diffuser.

Abstract translation: 用于燃气涡轮发动机的离心式叶轮组件的扩散器包括扩散器壳体，其具有在其中延伸的多个叶片，其限定与入口空间连通的多个周向分布的倾斜通道。 每个叶片包括限定在其吸入表面中的排气口，位于前缘附近。 扩散器壳体包括至少部分地通过每个排出口和前缘上游的入口空间之间的叶片中的每一个限定的被动流体连通，使得穿过排出口的空气通过在前缘的上游再循环到入口 空间增加扩散器的浪涌余量。

公开(公告)号：US08231341B2

公开(公告)日：2012-07-31

申请号：US12404573

申请日：2009-03-16

Applicant: Stephen A. Anderson ,  Ronald Trumper ,  Gary Weir

Inventor： Stephen A. Anderson ,  Ronald Trumper ,  Gary Weir

IPC: F04D29/02

CPC classification number: F04D29/542 ,  F02C3/08 ,  F02C9/52 ,  F04D17/025 ,  F04D29/284 ,  F04D29/403

Abstract: A hybrid gas compressor has at least one rotor and shroud which define a compressor gas path extending from an inlet to an outlet. The compressor includes at least two compression stages and one diffusion stage between the inlet and outlet, the compression stages including respective circumferential arrays of blades extending from the rotor and the diffusion stage including a circumferential array of vanes between the compression stages. Blade aerodynamic loadings may be controlled, particularly in the last stage, to provide desired compression characteristics across the compressor. A bleed outlet is optionally located between the inlet and outlet for bleeding from the gas path.

Abstract translation: 混合气体压缩机具有至少一个转子和护罩，其限定从入口延伸到出口的压缩机气体路径。 压缩机包括至少两个压缩级和在入口和出口之间的一个扩散级，压缩级包括从转子和扩散级延伸的相应的周向阵列，其包括在压缩级之间的周向阵列的叶片。 叶片空气动力学载荷可以被控制，特别是在最后阶段，以提供压缩机所需的压缩特性。 排气口可选地位于入口和出口之间，用于从气体路径渗出。

公开(公告)号：US20120128479A1

公开(公告)日：2012-05-24

申请号：US13362945

申请日：2012-01-31

Applicant: Janpeter KÜHNEL ,  Heinz-Jürgen FELD ,  Christine LINDBLOM

Inventor： Janpeter KÜHNEL ,  Heinz-Jürgen FELD ,  Christine LINDBLOM

IPC: F04D29/40

CPC classification number: F04D29/444 ,  F01D5/141 ,  F01D9/041 ,  F02C3/08 ,  F05D2220/40 ,  F05D2250/52

Abstract: The guide device for the diffusor at the compressor impeller outlet of a radial compressor has guide blades with stepped inlet edges. The step is implemented by setting back the hub-side inlet edge. This meridional stepping divides the guide blades into two component blades, of which the first component blade is made longer than the second component blade. The set-back of the inlet edge of the hub-side component blade and the associated superposition of the noise fields which are produced on the front and rear inlet edge of the diffusor leads to improvement of the acoustic properties of the compressor.

Abstract translation: 在径向压缩机的压缩机叶轮出口处的扩散器的引导装置具有带有阶梯式入口边缘的导向叶片。 该步骤是通过安装回路侧入口边缘来实现的。 该子午线步进将导向叶片分成两个组件叶片，其中第一组件叶片制成比第二组件叶片更长。 轮毂侧部件叶片的入口边缘的折回以及在扩散器的前部和后部入口边缘上产生的噪声场的相关叠加导致压缩机的声学特性的改善。

公开(公告)号：US08162604B2

公开(公告)日：2012-04-24

申请号：US11802530

申请日：2007-05-23

Applicant: Janpeter Kühnel ,  Heinz-J{dot over (u)}rgen Feld ,  Christine Lindblom

Inventor： Janpeter Kühnel ,  Heinz-J{dot over (u)}rgen Feld ,  Christine Lindblom

IPC: F04D29/30

CPC classification number: F04D29/444 ,  F01D5/141 ,  F01D9/041 ,  F02C3/08 ,  F05D2220/40 ,  F05D2250/52

Abstract: The guide device for the diffusor at the compressor impeller outlet of a radial compressor has guide blades with stepped inlet edges. The step is implemented by setting back the hub-side inlet edge. This meridional stepping divides the guide blades into two component blades, of which the first component blade is made longer than the second component blade. The set-back of the inlet edge of the hub-side component blade and the associated superposition of the noise fields which are produced on the front and rear inlet edge of the diffusor leads to improvement of the acoustic properties of the compressor.

Abstract translation: 在径向压缩机的压缩机叶轮出口处的扩散器的引导装置具有带有阶梯式入口边缘的导向叶片。 该步骤是通过安装回路侧入口边缘来实现的。 该子午线步进将导向叶片分成两个组件叶片，其中第一组件叶片制成比第二组件叶片更长。 轮毂侧部件叶片的入口边缘的折回以及在扩散器的前部和后部入口边缘上产生的噪声场的相关叠加导致压缩机的声学特性的改善。

公开(公告)号：US20110097204A1

公开(公告)日：2011-04-28

申请号：US12993949

申请日：2009-05-20

Applicant: Didier Hippolyte Hernandez ,  Romain Nicolas Lunel

Inventor： Didier Hippolyte Hernandez ,  Romain Nicolas Lunel

IPC: F04D29/44

CPC classification number: F02C3/08 ,  F01D9/045 ,  F01D25/246 ,  F04D29/023 ,  F04D29/444 ,  F05D2230/90 ,  F05D2250/52 ,  Y02T50/67 ,  Y02T50/671

Abstract: A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating.

Abstract translation: 包括环形燃烧室的涡轮机; 离心式压缩机; 具有径向定向的上游部分的环形扩散器，其具有连接到压缩机出口的扩散通道; 弯曲的中间部分; 以及具有一系列圆形间隔开的偏转叶片的下游部分。 涡轮机还包括外部围绕燃烧室和下游部分的外壳。 外壳的面向偏转器叶片的区域被可磨损材料的涂层覆盖，并且通过下游部分的流动通道由外壳和涂层限定在外部。

公开(公告)号：US20110064583A1

公开(公告)日：2011-03-17

申请号：US12990953

申请日：2009-05-14

Applicant: Geoffroy Louis-Henri Marie Billotey ,  Pierre Biscay ,  Gilles Cazenave-Larroche ,  Jean-Philippe Ousty

Inventor： Geoffroy Louis-Henri Marie Billotey ,  Pierre Biscay ,  Gilles Cazenave-Larroche ,  Jean-Philippe Ousty

IPC: F01D5/14

CPC classification number: F04D29/30 ,  F01D5/141 ,  F02C3/08 ,  F04D29/284 ,  F05D2250/14 ,  F05D2250/71 ,  F05D2260/94 ,  Y02T50/671 ,  Y02T50/673

Abstract: A compressor impeller including at least one blade connected to an impeller hub via a junction of curved shape, the blade extending along a defined chord between a leading edge and a trailing edge of the blade. The junction presents the shape of an ellipse that varies along the chord.

Abstract translation: 压缩机叶轮包括至少一个通过弯曲形状的连接件连接到叶轮毂的叶片，所述叶片沿着所述叶片的前缘和后缘之间的限定的弦延伸。 连接处呈现沿着和弦变化的椭圆形状。