FR3026438B1 - Procede pour arreter un moteur de giravion en survitesse, systeme et giravion associes - Google Patents

Procede pour arreter un moteur de giravion en survitesse, systeme et giravion associes

Info

Publication number
FR3026438B1
FR3026438B1 FR1402172A FR1402172A FR3026438B1 FR 3026438 B1 FR3026438 B1 FR 3026438B1 FR 1402172 A FR1402172 A FR 1402172A FR 1402172 A FR1402172 A FR 1402172A FR 3026438 B1 FR3026438 B1 FR 3026438B1
Authority
FR
France
Prior art keywords
derivative
stopping
current
giravion
therefor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR1402172A
Other languages
English (en)
Other versions
FR3026438A1 (fr
Inventor
Bernard Certain
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Helicopters SAS
Original Assignee
Airbus Helicopters SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Helicopters SAS filed Critical Airbus Helicopters SAS
Priority to FR1402172A priority Critical patent/FR3026438B1/fr
Priority to US14/867,464 priority patent/US10150569B2/en
Publication of FR3026438A1 publication Critical patent/FR3026438A1/fr
Application granted granted Critical
Publication of FR3026438B1 publication Critical patent/FR3026438B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
    • B64D31/02—Initiating means
    • B64D31/06—Initiating means actuated automatically
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/46—Emergency fuel control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/04—Purpose of the control system to control acceleration (u)
    • F05D2270/042—Purpose of the control system to control acceleration (u) by keeping it below damagingly high values
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/50—Control logic embodiments
    • F05D2270/52—Control logic embodiments by electrical means, e.g. relays or switches

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Control Of Transmission Device (AREA)
  • Protection Of Generators And Motors (AREA)

Abstract

La présente invention concerne un procédé pour arrêter un moteur (10) de giravion (1) en survitesse, ledit moteur (10) comprenant un générateur de gaz (11) et un ensemble de puissance (19). Lorsque ledit moteur (10) est en fonctionnement. on établit une loi donnant une dérivée limite qui varie en fonction de la vitesse de rotation de l'ensemble de puissance (19). On mesure la vitesse de rotation dite « vitesse courante » atteinte par l'ensemble de puissance et on détermine la dérivée par rapport au temps de ladite vitesse de rotation dite « dérivée courante. On arrête automatiquement ledit moteur (10) lorsque la dérivée limite correspondant à la vitesse courante selon ladite loi (100) est inférieure ou égale à la dérivée courante.
FR1402172A 2014-09-26 2014-09-26 Procede pour arreter un moteur de giravion en survitesse, systeme et giravion associes Active FR3026438B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1402172A FR3026438B1 (fr) 2014-09-26 2014-09-26 Procede pour arreter un moteur de giravion en survitesse, systeme et giravion associes
US14/867,464 US10150569B2 (en) 2014-09-26 2015-09-28 Method of stopping a rotorcraft engine in overspeed, and a system and a rotorcraft associated therewith

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1402172A FR3026438B1 (fr) 2014-09-26 2014-09-26 Procede pour arreter un moteur de giravion en survitesse, systeme et giravion associes

Publications (2)

Publication Number Publication Date
FR3026438A1 FR3026438A1 (fr) 2016-04-01
FR3026438B1 true FR3026438B1 (fr) 2019-03-15

Family

ID=51894104

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1402172A Active FR3026438B1 (fr) 2014-09-26 2014-09-26 Procede pour arreter un moteur de giravion en survitesse, systeme et giravion associes

Country Status (2)

Country Link
US (1) US10150569B2 (fr)
FR (1) FR3026438B1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3013390B1 (fr) * 2013-11-19 2019-01-25 Safran Helicopter Engines Turbomachine et procede de regulation
FR3034403B1 (fr) * 2015-03-31 2017-03-31 Airbus Helicopters Procede et dispositif pour arreter un turbomoteur en fonctionnement nominal
FR3049646B1 (fr) * 2016-03-31 2019-04-12 Safran Aircraft Engines Dispositif de limitation de survitesse d'un rotor de turbine de turbomachine
FR3076361B1 (fr) * 2018-01-04 2019-12-13 Safran Aircraft Engines Procede de filtrage adaptatif
FR3111668B1 (fr) 2020-06-17 2023-04-07 Airbus Helicopters Procédé pour arrêter un moteur en survitesse, système et giravion associés

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3899879A (en) * 1973-11-05 1975-08-19 Gen Motors Corp Turbine engine fuel control
US4423593A (en) * 1982-04-16 1984-01-03 Chandler Evans Inc. Fuel control for controlling helicopter rotor/turbine acceleration
JPH0466730A (ja) * 1990-07-09 1992-03-03 Toyota Motor Corp 二軸式ガスタービン機関の制御装置
FR2803051B1 (fr) * 1999-12-23 2002-05-03 Turbomeca Dispositif et procede de regulation de la puissance d'un groupe motopropulseur d'entrainement de rotor d'helicoptere
US6321525B1 (en) * 2000-02-03 2001-11-27 Rolls-Royce Corporation Overspeed detection techniques for gas turbine engine
JP2004011459A (ja) * 2002-06-04 2004-01-15 Ishikawajima Harima Heavy Ind Co Ltd 舶用２軸型ガスタービンの過回転防止装置とその方法
ATE438788T1 (de) * 2004-06-03 2009-08-15 Goodrich Pump & Engine Control Drehzahlbegrenzer für turbomotoren
FR2962165B1 (fr) 2010-07-02 2014-05-02 Turbomeca Detection de survitesse d'une turbine libre par mesure sur couplemetre
FR2967213B1 (fr) 2010-11-10 2012-10-26 Eurocopter France Procede de commande pour systeme de securite survitesse de moteurs d'aeronef et circuit de commande pour mettre en oeuvre ledit procede
FR2980174B1 (fr) * 2011-09-16 2013-10-18 Eurocopter France Procede de commande pour systeme de securite survitesse, systeme et aeronef associe
US9382847B2 (en) * 2012-11-02 2016-07-05 Pratt & Whitney Canada Corp. Rotor resonance disturbance rejection controller

Also Published As

Publication number Publication date
US20160090187A1 (en) 2016-03-31
FR3026438A1 (fr) 2016-04-01
US10150569B2 (en) 2018-12-11

Similar Documents

Publication Publication Date Title
FR3026438B1 (fr) Procede pour arreter un moteur de giravion en survitesse, systeme et giravion associes
BR0311844B1 (pt) dispositivo e método para limpeza de gás de cárter.
EA201992453A1 (ru) Система мониторинга для определения снижения работоспособности движительной подсистемы
WO2018102041A3 (fr) Caractérisation de système d'alimentation hybride
CN103148927B (zh) 一种在半消声室内进行发动机附件系统噪声测试系统
WO2012025434A3 (fr) Procédé de détection des défauts d'allumage dans des moteurs à combustion interne et dispositif de détection
ATE448022T1 (de) Gasreinigungsvorrichtung
PH12016000025A1 (en) Vehicular control apparatus
FR3025252B1 (fr) Dispositif et procede de demarrage d'une turbine a gaz, procede de regulation de la vitesse de rotation d'une turbine a gaz, et turbine a gaz et turbomoteur associes
MX2017004391A (es) Sistemas y métodos para monitoreo de nivel de combustible en un generador accionado por motor.
FR3034403A1 (fr) Procede et dispositif pour arreter un turbomoteur en fonctionnement nominal
WO2012143354A3 (fr) Dispositif et procédé de démarrage d'un moteur à combustion interne disposé dans un véhicule
JP2016084714A5 (fr)
US9983044B2 (en) Method for diagnosing a torque impulse generator
EP2787630A3 (fr) Détection de défaillances dans des moteurs et des entraînements
BRPI1102289A8 (pt) método de gestão para gerir um movimento de giro de uma aeronave taxiando no solo
FR3062422B1 (fr) Systeme d'alimentation en carburant d'une turbomachine
FR2985112B1 (fr) Onduleur de pilotage avec detecteur d'erreur de couple
EP2988398A3 (fr) Machine électrique rotative
FR3062881B1 (fr) Procede et systeme de commande d'un dispositif d'urgence
CN103057549B (zh) 铁路机车牵引特性曲线自动修正方法
FR3111668B1 (fr) Procédé pour arrêter un moteur en survitesse, système et giravion associés
AU2017267094A1 (en) Method for identifying snoring
TW200951418A (en) Eccentricity measuring method
EP2975241A3 (fr) Dispositif de commande de moteur

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20160401

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

PLFP Fee payment

Year of fee payment: 9

PLFP Fee payment

Year of fee payment: 10