公开(公告)号：EP3054125B1

公开(公告)日：2024-04-17

申请号：EP16154540.5

申请日：2016-02-05

IPC: F02C7/042 ,  F01D17/16 ,  F02C9/20 ,  F01D17/08 ,  F02C9/28 ,  F04D27/02

CPC classification number: F01D17/162 ,  F02C9/20 ,  F05D2270/09620130101 ,  F04D27/0246 ,  F01D17/08 ,  F05D2270/31220130101 ,  F02C9/28 ,  F05D2270/31120130101 ,  F05D2270/31320130101

公开(公告)号：EP3194729B1

公开(公告)日：2018-09-26

申请号：EP15797889.1

申请日：2015-11-06

Applicant: Siemens Aktiengesellschaft

Inventor： LARSON, Marco

IPC: F01D21/00 ,  F02C7/143 ,  F02C7/18 ,  F02C9/20

CPC classification number: F02C7/143 ,  F01D21/00 ,  F02C3/04 ,  F02C7/042 ,  F02C7/185 ,  F02C9/20 ,  F05D2220/32 ,  F05D2260/212 ,  F05D2270/303 ,  F05D2270/311

公开(公告)号：EP2809926B1

公开(公告)日：2018-09-19

申请号：EP13743341.3

申请日：2013-01-28

Applicant: United Technologies Corporation

Inventor： ROSE, Becky E. ,  BRILLIANT, Lisa I

IPC: F02C7/05

CPC classification number: B64D45/00 ,  B64D2033/022 ,  F01D17/162 ,  F02C7/05 ,  F02C9/20 ,  F04D27/0292 ,  F04D29/563 ,  F05D2270/114

Abstract: A method of protecting a gas turbine engine according an exemplary aspect of the present disclosure includes, among other things, the steps of determining at least one flight condition of an aircraft and comparing the at least one flight condition to a programmed condition. The method further includes the steps of moving a plurality of inlet vanes of a low pressure compressor from a first position to a second position if the step of comparing the at least one flight condition to the programmed flight condition determines the programmed flight condition are met and deflecting any foreign objects with the plurality of inlet vanes.

公开(公告)号：EP2481892B1

公开(公告)日：2018-08-29

申请号：EP12153325.1

申请日：2012-01-31

Applicant: United Technologies Corporation

Inventor： Gasmen, Eugene C. ,  Wiecko, Stanley

IPC: F01D17/16 ,  F01D25/24 ,  F02C9/20

CPC classification number: F01D17/162 ,  F01D25/243 ,  F01D25/246 ,  F02C9/20 ,  F05D2260/50 ,  F05D2270/60 ,  Y10T29/53

Abstract: A gas turbine engine (10) includes a synchronizing ring (34). A cradle (78) includes an integrally formed anti-rotation feature (82). The cradle (78) is secured to the synchronizing ring (34) and located relative thereto with the anti-rotation feature (82). A bumper (80) is slidably supported within the cradle (78). In one example, a bushing (48) is provided within a hole (90) in the bumper (80). A fastener (92) is inserted into the hole (90) and a bushing (48) to secure the bumper (80) to the synchronizing ring (34).

公开(公告)号：EP3324118A1

公开(公告)日：2018-05-23

申请号：EP17201029.0

申请日：2017-11-10

Applicant: General Electric Company

Inventor： SORATO, Sebastiano ,  AXFORD, Lindsay Dawn ,  GRIMM, Frank ,  LECHNER, Andreas ,  METTLER, Adrian

IPC: F23N1/00 ,  F23N5/00 ,  F23N5/02 ,  F23N5/16 ,  F23N5/24 ,  F23R3/28 ,  F02C9/48

CPC classification number: F02C9/28 ,  F02C7/042 ,  F02C9/20 ,  F02C9/48 ,  F05D2220/32 ,  F05D2220/72 ,  F05D2270/08 ,  F23N1/00 ,  F23N5/003 ,  F23N5/02 ,  F23N5/16 ,  F23N5/24 ,  F23N2037/02 ,  F23N2041/20 ,  F23R3/28 ,  F23R3/286 ,  Y02E20/16

Abstract: A combustor system (104) for a GT system may include: a plurality of burners (120, 120A-E, 120G, 1201, 120P), each burner (120, 120A-E, 120G, 1201, 120P) including an inflow region (124) for receiving a combustion air flow (126) and a mixing zone (128) disposed downstream of the inflow region (124) for receiving the air flow (126) and a fuel flow (130); a combustion chamber (105) disposed downstream of the mixing zone (128); a fuel flow valve system (140) disposed to control the fuel flow (130) to each of the plurality of burners (120, 120A-E, 120G, 1201, 120P); a combustion sensor (142) configured to determine a combustion parameter; and an exhaust sensor (144) configured to determine an exhaust parameter. A control system (160) may be connected to the combustion sensor (142), the exhaust sensor (144) and fuel flow valve system (140). The control system (160), in response to the gas turbine system (100) operating at a low partial load, redistributes the fuel flow (130) to at least one burner (120, 120A-E, 120G, 1201, 120P) of the plurality of burners (120, 120A-E, 120G, 1201, 120P) as a function of a predetermined emission limit.

公开(公告)号：EP2623718A3

公开(公告)日：2018-05-23

申请号：EP13151541.3

申请日：2013-01-16

Applicant: Honeywell International Inc.

Inventor： Morand, Nicolas ,  Espasa, Olivier ,  Abel, Francis ,  Sausse, Lorrain ,  Mailfert, Julien ,  Favray, Frederic ,  Bouvier, Emmanuel

IPC: F01D9/04 ,  F01D17/16 ,  F02C6/12 ,  F02C9/20

CPC classification number: F01D17/165 ,  F01D9/048 ,  F02C6/12 ,  F02C9/20 ,  Y10T29/49229

Abstract: An assembly can include vanes and a base configured to seat the vanes at a radial distance about an axis where each vane includes a leading edge and a trailing edge, a pair of lateral surfaces that meet at the leading edge and at the trailing edge, an extension that extends from one of the lateral surfaces and that has a contact surface, and a stop surface to form a contact with a contact surface of another vane to define a minimum flow distance between the vane and the other vane. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

公开(公告)号：EP3293385A1

公开(公告)日：2018-03-14

申请号：EP17189489.2

申请日：2017-09-05

Applicant: United Technologies Corporation

Inventor： TEICHOLZ, Matthew D. ,  HATCH, Stewart B. ,  DAENTL, Wyatt S.

IPC: F02C9/18 ,  F02C9/20 ,  F04D27/02

CPC classification number: B64D31/06 ,  B64D27/10 ,  F01D5/02 ,  F01D17/105 ,  F01D17/145 ,  F01D17/162 ,  F02C9/18 ,  F02C9/20 ,  F04D25/045 ,  F04D27/001 ,  F04D29/321 ,  F05D2220/323 ,  F05D2260/80 ,  F05D2270/02 ,  F05D2270/04 ,  F05D2270/101 ,  F05D2270/102 ,  F05D2270/1024 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/309 ,  F05D2270/54

Abstract: A control system (100) for a gas turbine engine includes a processing system (102) operable to control a speed of the gas turbine engine and a memory system (104). The memory system (104) is operable to store instructions executable by the processing system (102) to determine at least one performance parameter associated with a stall condition of the gas turbine engine and to incrementally adjust an acceleration rate of the gas turbine engine based on detecting a degraded stall line limit according to the at least one performance parameter.

Abstract translation: 用于燃气涡轮发动机的控制系统（100）包括可操作以控制燃气涡轮发动机和存储器系统（104）的速度的处理系统（102）。 存储器系统（104）可操作以存储可由处理系统（102）执行的指令以确定与燃气涡轮发动机的失速状况相关联的至少一个性能参数并且基于以下参数递增地调节燃气涡轮发动机的加速率： 根据所述至少一个性能参数检测退化的失速线限制。

公开(公告)号：EP2235329A4

公开(公告)日：2018-02-21

申请号：EP07852145

申请日：2007-12-20

Applicant: GKN AEROSPACE SWEDEN AB

Inventor： LUNDBLADH ANDERS

IPC: F01D17/16 ,  F01D9/02 ,  F02C3/067 ,  F02C7/32 ,  F02C9/20 ,  F04D19/02 ,  F04D29/56

CPC classification number: F02C3/067 ,  F01D17/162 ,  F02C7/32 ,  F02C9/20 ,  F04D19/024 ,  F04D29/563 ,  F05D2270/061

Abstract: A gas turbine engine includes in serial flow relationship: a first compressor provided with at least one row of compressor blades distributed circumferentially around the first compressor; a combustion chamber; and a first turbine provided with at least one row of turbine blades distributed circumferentially around the first turbine, wherein the first compressor and the first turbine are rotationally rigidly connected by a first shaft. The first turbine is adapted to influence a gas flow rate through the gas turbine engine depending on a rotational speed of the first turbine, wherein the gas turbine engine further includes an arrangement for controlling the rotational speed of the first turbine. A method for controlling a gas flow rate in an axial flow gas turbine engine is also provided.

公开(公告)号：EP3061919B1

公开(公告)日：2017-11-22

申请号：EP15156245.1

申请日：2015-02-24

Applicant: Ansaldo Energia Switzerland AG

Inventor： Engesser, Hermann

IPC: F01D13/02 ,  F01D15/10 ,  F01D19/00 ,  F01D21/00 ,  F02C6/02 ,  F02C9/20 ,  F02C9/28

CPC classification number: F01D15/10 ,  F01D13/02 ,  F01D19/00 ,  F01D21/00 ,  F02C6/02 ,  F02C9/20 ,  F02C9/28 ,  F05D2220/60 ,  F05D2220/72 ,  F05D2220/764 ,  F05D2270/101 ,  F05D2270/304 ,  H02K7/1823 ,  H02P9/04

Abstract: The invention concerns a method for operating a gas turbine arrangement, wherein the gas turbine arrangement being actively connected to a grid system and comprising a separation of compressor and turbine shaft to operate both components individually as unit. A first unit comprising at least one turbine (T) and at least one generator (G) and a second unit comprising at least one compressor (C) and least one motor (M). Various switches (S1, S2, S3) are situated along power lines (100, 400, 600) and being actively connected to a frequency converter (FC) and/or the grid system, wherein the compressed air duct (700) operating downstream of the compressor (C) comprising a flap (Fl). The operating of the gas turbine arrangement refers to the following modes: standstill mode; ready-to-start mode; start-up and ignition mode; loading mode; shout-down mode; GT trip mode.

公开(公告)号：EP3239500A1

公开(公告)日：2017-11-01

申请号：EP17167847.7

申请日：2017-04-24

Applicant: General Electric Company

Inventor： SINGH, Anurag ,  DI PALMA, Steven

IPC: F02C9/20

CPC classification number: G05B19/4097 ,  F02C9/20 ,  F05D2220/3213 ,  F05D2260/81 ,  F05D2270/20 ,  F05D2270/303 ,  G05B2219/42155 ,  G05B2219/50068

Abstract: Embodiments of the present disclosure include methods, systems, and program products for controlling a machine (100). Methods according to the present disclosure can include: calculating, using a performance model (306) of the machine (100), a set of inter-stage conditions (152A-E) of the machine (100) corresponding to one of a set of input conditions (302) and a set of output conditions (304) during an operation of the machine (100), wherein the machine (100) includes a turbine component having a fluid path therein traversing a plurality of turbine stages and a plurality of inter-stage positions (152A-E); calibrating the performance model (228) of the machine (100) based on a difference between a predicted value in the performance model (306) of the machine (100) and one of the set of input conditions (302) and the set of output conditions(304); and adjusting an operating parameter of the machine (100) based on the calibrated performance model (228) and the calculated set of inter-stage conditions (152A-E) of the machine (100).

Abstract translation: 本公开的实施例包括用于控制机器（100）的方法，系统和程序产品。 根据本公开的方法可以包括：使用机器（100）的性能模型（306）计算机器（100）的一组级间条件（152A-E），其对应于一组 在机器（100）的操作期间输入条件（302）和一组输出条件（304），其中机器（100）包括涡轮部件，涡轮部件具有穿过多个涡轮级的流体路径以及多个涡轮级 阶段位置（152A-E）; 基于所述机器（100）的所述性能模型（306）中的预测值与所述一组输入条件（302）中的一个和所述一组输出条件（302）之间的差来校准所述机器（100）的所述性能模型（228） 条件（304）; 以及基于所校准的性能模型（228）和机器（100）的所计算的一组级间条件（152A-E）来调整机器（100）的操作参数。