公开(公告)号：US09771870B2

公开(公告)日：2017-09-26

申请号：US14635552

申请日：2015-03-02

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Douglas D. Dierksmeier

IPC: F01D5/08 ,  F02C7/28 ,  F01D5/14 ,  F01D5/20 ,  F01D5/30 ,  F01D11/08 ,  F01D11/12 ,  F01D11/14 ,  F01D11/16 ,  F01D11/20 ,  F01D11/22 ,  F01D11/00 ,  F01D5/22

CPC classification number: F02C7/28 ,  F01D5/085 ,  F01D5/147 ,  F01D5/20 ,  F01D5/225 ,  F01D5/3007 ,  F01D11/001 ,  F01D11/006 ,  F01D11/08 ,  F01D11/12 ,  F01D11/14 ,  F01D11/16 ,  F01D11/20 ,  F01D11/22 ,  F05D2220/32 ,  Y02T50/672 ,  Y02T50/676

Abstract: A blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.

公开(公告)号：US09719366B2

公开(公告)日：2017-08-01

申请号：US13916179

申请日：2013-06-12

Applicant: General Electric Company

Inventor： Lijie Yu ,  Venkatesh Rajagopalan ,  Sachin Srivastava ,  Mayank Lalan

IPC: F01D11/14 ,  F01D11/20 ,  F01D17/02 ,  F01D21/00 ,  F01D21/04 ,  F01D21/10 ,  F01D21/14

CPC classification number: F01D11/14 ,  F01D11/20 ,  F01D17/02 ,  F01D21/003 ,  F01D21/04 ,  F01D21/045 ,  F01D21/10 ,  F01D21/14

Abstract: Systems and methods for blade health monitoring are provided. According to one embodiment of the disclosure, a system may include a feature extraction module and an anomaly detection module in communication with the extraction module. The feature extraction module may be configured to continuously receive blade passing signal data associated with clearance of a blade and pre-process the blade passing signal data. Blade clearance feature data may be extracted from the blade passing signal data prior to transmission to the anomaly detection module. The anomaly detection module may be configured to normalize the blade clearance feature data received from the extraction module, analyze the blade clearance feature data to detect a shift in the clearance of the blade, and determine an abnormality of the blade based on the shift exceeding a predetermined shift threshold.

公开(公告)号：US09631510B2

公开(公告)日：2017-04-25

申请号：US14379636

申请日：2013-02-13

Applicant: HANWHA TECHWIN CO., LTD.

Inventor： Chan-sun Lim

IPC: F01D11/14 ,  F02C7/28 ,  F01D11/10 ,  F01D11/20 ,  F02C3/20 ,  F02C9/40

CPC classification number: F01D11/14 ,  F01D11/10 ,  F01D11/20 ,  F02C3/20 ,  F02C7/28 ,  F02C9/40

Abstract: According to an aspect of an exemplary embodiment, there is provided a turbine seal assembly comprising: a seal installation groove formed inside a casing; at least one seal member that has at least one tip portion formed in a blade direction and is installed in the seal installation groove; at least one elastic member for elastically connecting the casing to the seal member, wherein an inlet for an inflow of compressed gas is formed in the seal installation groove, and wherein a first space which the compressed gas enters is formed in the seal member, and at least one flow pathway which connects the first space to a space between a blade and the seal member is formed in the seal member.

公开(公告)号：US20170067354A1

公开(公告)日：2017-03-09

申请号：US14848419

申请日：2015-09-09

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D11/00 ,  F01D11/08 ,  F01D9/02 ,  F01D5/12 ,  F23R3/00 ,  F02C7/28

CPC classification number: F01D11/003 ,  F01D5/12 ,  F01D9/02 ,  F01D11/00 ,  F01D11/005 ,  F01D11/08 ,  F01D11/14 ,  F01D11/20 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/35 ,  F05D2260/52 ,  F16J15/028 ,  F16J15/061 ,  F23R3/002 ,  Y02T50/672 ,  Y02T50/6765

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier and configured to abut against at least two sealing surfaces. A method of sealing between adjacent components of a gas turbine engine is also disclosed.

Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的密封组件包括壳体，固定到壳体并被构造成被选择性地从壳体偏置的密封承载件，以及固定到密封件的楔形密封件 并且构造成抵靠至少两个密封表面。 还公开了一种在燃气涡轮发动机的相邻部件之间的密封方法。

公开(公告)号：US20170058687A1

公开(公告)日：2017-03-02

申请号：US15184692

申请日：2016-06-16

Applicant: TECHSPACE AERO S.A.

Inventor： STÉPHANE HIERNAUX

IPC: F01D11/04 ,  F01D11/14 ,  F01D11/10

CPC classification number: F01D11/04 ,  F01D11/10 ,  F01D11/14 ,  F04D27/0215 ,  F04D27/0238 ,  F04D29/526 ,  F04D29/685 ,  F05D2220/32 ,  F05D2240/55

Abstract: The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.

Abstract translation: 本申请提出了一种轴向涡轮机压缩机，其包括具有至少一个环形排的转子叶片的转子，围绕该行转子叶片的定子壳体，壳体包括用于产生反涡流的装置。 在压缩机运行期间，叶片的运动在叶片尖端产生泄漏涡流。 发电装置又将与涡流相反的方向旋转的反涡流喷射以抵消泄漏涡流。 这提高了压缩机的浪涌裕度。 本申请还提供了一种通过反涡流喷射来控制涡轮机压缩机的稳定性的方法。

公开(公告)号：US20160356169A1

公开(公告)日：2016-12-08

申请号：US14731140

申请日：2015-06-04

Applicant: United Technologies Corporation

Inventor： Brian Duguay ,  Timothy M. Davis

IPC: F01D11/22

CPC classification number: F01D11/22 ,  F01D11/14 ,  F01D11/20

Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly includes a blade outer air seal segment, a linkage, a rocker arm and an actuation device. The linkage is attached to the blade outer air seal segment. The rocker arm includes a first arm and a second arm engaged with the linkage. The actuation device is engaged with the first arm. The actuation device is configured to pivot the rocker arm and thereby radially move the blade outer air seal segment.

Abstract translation: 为具有轴向中心线的涡轮发动机提供组件。 该涡轮发动机组件包括叶片外部空气密封段，连杆机构，摇臂和致动装置。 连接件连接到叶片外部空气密封段。 摇臂包括与连杆相配合的第一臂和第二臂。 致动装置与第一臂接合。 致动装置构造成枢转摇臂，从而径向移动叶片外部空气密封段。

公开(公告)号：US20160319697A1

公开(公告)日：2016-11-03

申请号：US15030317

申请日：2015-01-15

Applicant: United Technologies Corporation

Inventor： John Akin

IPC: F01D25/12 ,  F01D25/24 ,  H01L35/32 ,  B64D41/00 ,  F25B21/02 ,  F02C7/12 ,  F01D11/14

CPC classification number: F01D25/12 ,  B64D41/00 ,  F01D11/14 ,  F01D25/24 ,  F02C7/12 ,  F02K1/28 ,  F02K1/822 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/80 ,  F25B21/02 ,  F25B2321/0212 ,  F25B2321/023 ,  F25B2321/0251 ,  H01L35/32 ,  Y02T50/675

Abstract: An aircraft jet propulsion system may comprise a thermoelectric cooler array coupled to a portion thereof, wherein the TEC array converts electrical energy to heat energy to create a temperature gradient and cools a turbine case using the temperature difference of the TEC array. The system may include a controller configured to control an input power provided to each TEC of the array of TECs, such that the array of TECs facilitates controlled cooling of the aircraft jet propulsion system in response to the input power provided to each TEC of the array of TECs. The TEC array may be powered by an alternator or by a thermoelectric generator.

Abstract translation: 飞机喷射推进系统可以包括耦合到其一部分的热电冷却器阵列，其中TEC阵列将电能转换成热能以产生温度梯度并且使用TEC阵列的温度差来冷却涡轮机壳体。 该系统可以包括被配置为控制提供给TEC阵列的每个TEC的输入功率的控制器，使得TEC阵列响应于提供给阵列的每个TEC的输入功率而有助于飞行器喷射推进系统的受控冷却 的TECs。 TEC阵列可以由交流发电机或热电发电机供电。

公开(公告)号：US09422824B2

公开(公告)日：2016-08-23

申请号：US13654689

申请日：2012-10-18

Applicant: General Electric Company

Inventor： Matthew Stephen Casavant ,  Kenneth Damon Black ,  David Martin Johnson ,  Radu Ioan Danescu

IPC: F01D11/24 ,  F01D11/16 ,  F01D11/02 ,  F01D11/18 ,  F01D11/20 ,  F01D11/14

CPC classification number: F01D11/24 ,  F01D11/025 ,  F01D11/14 ,  F01D11/16 ,  F01D11/18 ,  F01D11/20 ,  F01D25/14 ,  F01D25/26 ,  F02C7/12

Abstract: Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.

Abstract translation: 通过从压缩机供给热控制气体到外壳和内壳之间的空间，为燃气轮机壳体提供热控制，并且通过多个孔将热控制气体从空间传递通过内壳体中的开口 通过附接到内壳的外表面的板限定。 孔以预定的不均匀分布布置，其对应于期望的优先冲击图案以提供不均匀的热传递。 燃气轮机热控制组件包括在燃气轮机运行期间通过从内壳的径向外侧到燃气轮机内部的热控制气体流动路径，从内壳提供优先传热的结构。

公开(公告)号：US20160208682A1

公开(公告)日：2016-07-21

申请号：US15083782

申请日：2016-03-29

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Shohei Naruoka ,  Hisatoyo Arima

IPC: F02B39/04 ,  F01D25/28 ,  F01D5/02 ,  F02D23/00

CPC classification number: F02B39/04 ,  F01D5/025 ,  F01D5/027 ,  F01D5/04 ,  F01D11/14 ,  F01D25/16 ,  F01D25/28 ,  F02B33/40 ,  F02B39/12 ,  F02C6/12 ,  F02D23/005 ,  F05D2220/40 ,  F05D2260/40311

Abstract: A rotary unit is rotatably accommodated within a supercharger casing of a supercharger for pressurizing an intake air of an engine. The rotary unit includes a supercharger rotary shaft, an impeller fixed to a tip end portion of the supercharger rotary shaft, a rotating component rotatable together with the supercharger rotary shaft independently of the impeller, and a nut member for pressing the impeller and the rotating component in a direction axially of the supercharger rotary shaft to thereby fix them to the supercharger rotary shaft. The nut member is formed with an adjustment portion for the rotational balance adjustment.

Abstract translation: 旋转单元可旋转地容纳在用于对发动机的进气加压的增压器的增压器壳体内。 旋转单元包括增压器旋转轴，固定到增压器旋转轴的前端部的叶轮，与增压器旋转轴独立于叶轮一起旋转的旋转部件，以及用于按压叶轮和旋转部件的螺母构件 在增压器旋转轴的轴向方向上，将其固定在增压器旋转轴上。 螺母构件形成有用于旋转平衡调节的调节部分。

公开(公告)号：US20160201496A1

公开(公告)日：2016-07-14

申请号：US14910035

申请日：2014-08-05

Applicant: SIEMENS AKTIENGESELLSCHAFT

Inventor： Fathi Ahmad ,  Michael Händler ,  Kevin Kampka ,  Christian Kowalski ,  Christian Kowalzik ,  Nihal Kurt ,  Stefan Schmitt ,  Peter Schröder

IPC: F01D11/08 ,  F02C3/04 ,  F01D25/28

CPC classification number: F01D11/08 ,  F01D5/143 ,  F01D11/14 ,  F01D25/28 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/83 ,  Y02T50/673

Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Abstract translation: 燃气轮机包括用于紧固到燃气轮机的涡轮机的环段主体的插入元件。 环形部体在热气体侧具有凹部。 插入元件设计成覆盖凹部。 插入元件包括具有凹入形状的前侧和后侧的盖板，以及设置在后侧的至少一个脚，用于定位在环形段主体上。 安装方法包括将插入元件固定到燃气轮机的涡轮机的环形段主体的凹部处的插入元件。