公开(公告)号：US20040055273A1

公开(公告)日：2004-03-25

申请号：US10441106

申请日：2003-05-20

Applicant: KABUSHIKI KAISHA TOSHIBA

Inventor： Kaiichirou Hirayama ,  Tadashi Kobayashi ,  Sayoko Kobayashi ,  Yuka Kobayashi ,  Hirokazu Kobayashi ,  Tomoo Katauri ,  Yasuhiko Ootsuki ,  Takashi Mizuno

IPC: F02C009/28

CPC classification number: F02C9/54 ,  F02C9/28 ,  F02C9/32 ,  F05D2270/024 ,  F05D2270/042 ,  F05D2270/06 ,  F05D2270/061 ,  F05D2270/091 ,  F05D2270/095 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/42 ,  G05B23/0291 ,  Y02T50/67

Abstract: A gas turbine control system is disclosed which operates to stabilize the system frequency in a case of transitional variations of the system frequency without making the strength of hot gas path parts of the gas turbine below a maximum stress value of the hot gas path parts. When a system frequency abnormality is detected, the output of the gas turbine is adjusted to recover the system frequency by making a gas turbine combustion gas temperature control inoperative. For this purpose, there are provided a logical circuit operative to make the gas turbine combustion gas temperature control disabled or inoperative in response to an abnormal system frequency detection signal, and a recovery circuit that operates to cancel the inoperative state of the gas turbine combustion gas temperature control. The detection of an abnormal system frequency may be carried out by an outside signal. An abnormality detection unit may be provided in a combined cycle plant.

Abstract translation: 公开了一种燃气轮机控制系统，其操作以在系统频率的过渡变化的情况下稳定系统频率，而不使燃气涡轮机的热气体路径部分的强度低于热气体路径部分的最大应力值。 当检测到系统频率异常时，通过使燃气轮机燃烧气体温度控制不起作用来调节燃气轮机的输出以恢复系统频率。 为此，提供了一种逻辑电路，其可操作以响应于异常的系统频率检测信号而使燃气轮机燃烧气体温度控制无效或不起作用;以及恢复电路，其操作以消除燃气轮机燃烧气体的不工作状态 温度控制。 异常系统频率的检测可以通过外部信号来执行。 可以在联合循环设备中提供异常检测单元。

公开(公告)号：US20030024235A1

公开(公告)日：2003-02-06

申请号：US09919029

申请日：2001-07-31

Inventor： Alan David Pisano ,  James Patrick Conaty ,  Matthew William Wiseman ,  Sabrina Anne Sequeira

IPC: B64G009/00

CPC classification number: F01D21/14 ,  F02C9/28 ,  F02C9/46 ,  F05D2220/323 ,  F05D2270/044 ,  F05D2270/051 ,  F05D2270/095 ,  F05D2270/12 ,  F05D2270/301 ,  F05D2270/304

Abstract: A control strategy for a gas turbine engine which exchanges future lifetime of the engine for present thrust. Gas turbine engines, such as those used in aircraft, sometimes incur damage, as when they ingest birds, or are struck with ballistic objects fired by an enemy. The invention detects the damage, and invokes a control strategy wherein the engine is operated in a more harsh manner, thereby sacrificing a significant part of the remaining lifetime of the engine, in order to obtain thrust currently.

公开(公告)号：US20030017046A1

公开(公告)日：2003-01-23

申请号：US09907138

申请日：2001-07-17

Inventor： Jack R. Little JR.

IPC: F03D001/00

CPC classification number: F01D21/20 ,  F01D21/003 ,  F01D21/16 ,  F05D2210/12 ,  F05D2210/31 ,  F05D2260/80 ,  F05D2270/095 ,  Y02T50/671

Abstract: A turbine controls testing device is disclosed that can be adapted to test the control systems of most turbine rotors without the use of steam. The turbine controls testing device comprises an operator control system, a drive motive power assembly and a purge gas assembly. The novel device controllably spins, accelerates, and decelerates a turbine with a relatively high level of precision, minimizing the likelihood that, in the event an overspeed mechanism malfunction occurs, the turbine will be damaged as a result of sonic velocity or any other mechanical failure.

Abstract translation: 公开了一种涡轮机控制测试装置，其可以适于在不使用蒸汽的情况下测试大多数涡轮转子的控制系统。 涡轮机控制测试装置包括操作员控制系统，驱动动力组件和吹扫气体组件。 新颖的装置以相当高的精度可控制地旋转，加速和减速涡轮机，最小化在发生超速机构故障的情况下，由于声速或任何其他机械故障，涡轮机将被损坏的可能性 。