公开(公告)号：US20180209347A1

公开(公告)日：2018-07-26

申请号：US15410996

申请日：2017-01-20

Applicant: HAMILTON SUNDSTRAND CORPORATION

Inventor： Myles R. Kelly ,  Robert Goodman ,  Michael D. Greenberg

IPC: F02C7/26 ,  F16K1/32 ,  F02C9/20

CPC classification number: F02C7/26 ,  F01D17/141 ,  F01D19/02 ,  F01D25/34 ,  F02C7/277 ,  F02C9/20 ,  F05D2250/311 ,  F05D2260/38 ,  F05D2260/53 ,  F05D2260/56 ,  F05D2260/84 ,  F05D2260/85 ,  F05D2270/095 ,  F05D2270/62 ,  F16K1/123 ,  F16K1/126 ,  F16K31/143 ,  F16K31/52 ,  F16K31/54 ,  F16K35/04

Abstract: A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between the first and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between first end and center portion, the first piston configured to block airflow through the fluid passage when in a closed position and allow airflow through the fluid passage when in an open position; a second piston located within the housing between second end and center portion, the second piston configured to block airflow through the fluid passage when in a closed position and allow airflow through the fluid passage when in an open position; and a manual override system configured to move from closed to open position at least one of the first and second pistons.

公开(公告)号：US09932906B2

公开(公告)日：2018-04-03

申请号：US14863140

申请日：2015-09-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Yufei Xiong ,  Dave Faymon ,  Scot Coffey

IPC: F02C9/28 ,  F02C9/46 ,  F02C9/54

CPC classification number: F02C9/28 ,  F02C9/46 ,  F02C9/54 ,  F05D2260/80 ,  F05D2270/021 ,  F05D2270/095

Abstract: A system and method of detecting an uncontrolled high thrust (UHT) condition in a turbofan gas turbine engine includes processing data to determine when a current commanded fan speed value is greater than a predetermined speed value. A current UHT commanded fan speed value is processed to determine if it will cause a target fan speed value to increase, remain steady, or decrease. The target fan speed value is set equal to the current UHT commanded fan speed value when the current UHT commanded fan speed value will cause the target fan speed value to increase or remain steady, and to a deceleration threshold value when the current UHT commanded fan speed value will cause the target fan speed value to decrease. An uncontrolled high thrust alert signal is generated when actual engine fan speed exceeds the target fan speed value by a predetermined amount for a preset time period.

公开(公告)号：US08321120B2

公开(公告)日：2012-11-27

申请号：US12355395

申请日：2009-01-16

Applicant: Harold Riley

Inventor： Harold Riley

IPC: G06G7/64

CPC classification number: F02C7/26 ,  F01D21/12 ,  F01D21/14 ,  F05D2270/09 ,  F05D2270/095

Abstract: A system and method are provided for controlling the start-up of a gas turbine engine having an exhaust gas temperature (EGT) sensor. A determination is made as to whether the EGT sensor is available or unavailable. The gas turbine engine is commanded to accelerate at a nominal acceleration rate during the start-up operation if the EGT sensor is available, and to accelerate at an off-nominal acceleration rate during the start-up operation if the EGT sensor is unavailable. The off-nominal acceleration rate is lower than the nominal acceleration rate.

Abstract translation: 提供了一种用于控制具有排气温度（EGT）传感器的燃气涡轮发动机起动的系统和方法。 确定EGT传感器是可用还是不可用。 如果EGT传感器可用，则燃气涡轮发动机被命令以启动操作期间的标称加速度加速，并且如果EGT传感器不可用，则在启动操作期间以非标称加速度加速。 标称加速度低于额定加速度。

公开(公告)号：US20040040279A1

公开(公告)日：2004-03-04

申请号：US10452922

申请日：2003-06-03

Inventor： Stefano Groppi ,  Andrea Casoni

IPC: F02C009/28

CPC classification number: F02C9/54 ,  F01D17/162 ,  F02C9/22 ,  F02C9/28 ,  F05D2270/083 ,  F05D2270/095 ,  F05D2270/112 ,  F05D2270/54 ,  F23N5/02 ,  F23N5/18 ,  F23N2023/36 ,  F23N2041/20

Abstract: In order to limit the flame temperature peaks following sudden load variations, corresponding control is planned of the position of the blades (13) of the distributor with variable geometry, of a single-shaft gas turbine (18); in particular, the control system proposed comprises a direct-action regulator (21) consisting of a calculation unit (22), which implements the simplified running model of the gas turbine (18), and a feedback regulator (20), which makes it possible to recuperate any inaccuracies of the direct-action regulator (21), caused by variations of the performance of the turbine (18), relative to those planned by the model, or caused by modelling errors.

Abstract translation: 为了在突然的负载变化之后限制火焰温度峰值，对单轴燃气轮机（18）的可变几何形状的分配器的叶片（13）的位置进行相应的控制; 特别地，提出的控制系统包括由实现燃气轮机（18）的简化运行模型的计算单元（22）和反馈调节器（20）组成的直动调节器（21），其使得 可能恢复直接作用调节器（21）的不正确性，这是由于涡轮机（18）的性能的变化，相对于由模型计划的或由建模误差引起的。

公开(公告)号：US06582184B2

公开(公告)日：2003-06-24

申请号：US09907138

申请日：2001-07-17

Applicant: Jack R. Little, Jr.

Inventor： Jack R. Little, Jr.

IPC: F01D2102

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.

公开(公告)号：US20240254929A1

公开(公告)日：2024-08-01

申请号：US18423639

申请日：2024-01-26

Applicant: Airbus Operations SAS

Inventor： Thierry IMMORDINO ,  Guillaume ALIX ,  David BOYER ,  Gilian ANTONIO ,  Bilal GUENCHI

IPC: F02C9/46 ,  F02C9/28

CPC classification number: F02C9/46 ,  F02C9/28 ,  F05D2220/323 ,  F05D2270/094 ,  F05D2270/095

Abstract: A blocking device for preventing an inappropriate shut-off of an engine of an aircraft. The blocking device enables by default the actuation of the shut-off unit and receives information representative of an activated or inactivated state of a fuel shut-off lever, of a reduced or non-reduced speed state of a throttle lever, and a correct or incorrect operating state of the engine. The blocking device blocks the actuation of the shut-off unit when the throttle lever is in an inactivated state, when the engine is in a correct operating state, and when, in addition, the throttle lever is in a non-reduced speed state or the throttle lever is in a reduced speed state and, in addition, the opposite propulsion engine is in a failed state or in an incorrect operating state.

公开(公告)号：US20170211413A1

公开(公告)日：2017-07-27

申请号：US15327630

申请日：2015-07-21

Applicant: Safran Electronics & Defense ,  Safran Helicopter Engines

Inventor： Michael MONTOYA ,  Nicolas MARTI ,  Stephen LANGFORD ,  Rafael SAMSON

IPC: F01D21/02 ,  B64D37/32 ,  F02C9/46 ,  F02C7/22 ,  F02C9/28

CPC classification number: F01D21/02 ,  B64D37/32 ,  F01D21/14 ,  F02C7/22 ,  F02C7/232 ,  F02C7/26 ,  F02C9/26 ,  F02C9/28 ,  F02C9/46 ,  F05D2270/021 ,  F05D2270/022 ,  F05D2270/09 ,  F05D2270/091 ,  F05D2270/092 ,  F05D2270/095 ,  F05D2270/304

Abstract: The invention relates to an overspeed protection device of an aircraft engine

公开(公告)号：US20120317955A1

公开(公告)日：2012-12-20

申请号：US13493433

申请日：2012-06-11

Applicant: Arthur L. ROWE ,  Christopher REDFERN

Inventor： Arthur L. ROWE ,  Christopher REDFERN

IPC: F02C3/00

CPC classification number: F01D21/06 ,  F01D17/162 ,  F02C9/54 ,  F04D27/0246 ,  F04D27/0292 ,  F05D2270/09 ,  F05D2270/095 ,  F05D2270/101

Abstract: A gas turbine engine control system comprising a variable stator vane schedule for normal operation of the gas turbine engine. The system is configured to generate an arm signal indicating potential shaft break. Then the system is configured to alter the variable stator vane schedule to slew each variable stator vane to decrease the available surge margin in response to the arm signal. Or the system is configured to limit a response rate of a variable stator vane actuator in response to the arm signal. Or the system is configured to alter the variable stator vane schedule and limit the response rate of the actuator.

Abstract translation: 一种燃气涡轮发动机控制系统，包括用于燃气涡轮发动机的正常操作的可变定子叶片调度。 该系统被配置为产生指示潜在轴断裂的臂信号。 然后，该系统被配置为改变可变定子叶片调度以旋转每个可变定子叶片，以响应于臂信号减小可用浪涌余量。 或者该系统被配置为响应于臂信号来限制可变定子叶片致动器的响应速率。 或者该系统被配置为改变可变定子叶片调度并限制致动器的响应速率。

公开(公告)号：US07340901B2

公开(公告)日：2008-03-11

申请号：US11594503

申请日：2006-11-07

Applicant: Harold J. Riley

Inventor： Harold J. Riley

IPC: F02C9/28

CPC classification number: F02C7/26 ,  F02C9/28 ,  F05D2220/50 ,  F05D2270/021 ,  F05D2270/095 ,  F05D2270/112 ,  F05D2270/3032 ,  F05D2270/705

Abstract: Conventional auxiliary power units (APUs) may experience over-temperature shutdowns when attempting to start them at high altitudes. Further, such conventional APUs may also experience overspeed conditions when a generator load is removed during on-speed operations. A fuel control logic that controls the fuel flow cutback below the minimum blowout fuel schedule is provided. A temperature trim loop measures engine temperature to determine the onset of a possible over-temperature condition. The fuel flow may then be trimmed accordingly to correct this over-temperature onset. Further, when the onset of an overspeed condition is detected, such as when a generator load is removed, the fuel flow may be trimmed accordingly to correct this overspeed onset. The fuel control logic allows the control to find the individual minimum fuel flow for each fuel control without risking blowout of the APU itself.

公开(公告)号：US06945030B2

公开(公告)日：2005-09-20

申请号：US10441106

申请日：2003-05-20

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

Inventor： Tadashi Kobayashi

IPC: F02C7/042 ,  F02C9/28 ,  F02C9/46 ,  F02C9/54 ,  F04D27/00 ,  F04D29/56 ,  G05B23/02 ,  H02P9/04 ,  F02C9/50

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。