EP0046698B1 - Procédé et dispositif de détection de décollement tournant - Google Patents

Procédé et dispositif de détection de décollement tournant Download PDF

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Publication number
EP0046698B1
EP0046698B1 EP81401162A EP81401162A EP0046698B1 EP 0046698 B1 EP0046698 B1 EP 0046698B1 EP 81401162 A EP81401162 A EP 81401162A EP 81401162 A EP81401162 A EP 81401162A EP 0046698 B1 EP0046698 B1 EP 0046698B1
Authority
EP
European Patent Office
Prior art keywords
signal
detector
comparator
supplied
rotary
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.)
Expired
Application number
EP81401162A
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German (de)
English (en)
French (fr)
Other versions
EP0046698A1 (fr
Inventor
Pierre Edouard Deneux
Patrick Jean Faure
Denis René Guy Laffitte
Michel Eugène Marcel Lemaoult
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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Publication of EP0046698A1 publication Critical patent/EP0046698A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring

Definitions

  • the present invention relates to a method for detecting a rotating detachment in a turbomachine having two rotating bodies: a high pressure body and a low pressure body, method of the type according to which the speed of rotation of each of said bodies is measured.
  • the gas turbine engine illustrated in Figure 1 is an example of the different types of engines for which the present invention can be used.
  • the invention also relates to a rotating detachment detection device.
  • Document US-A-2 918 790 thus describes a system for regulating a turbomachine of the double body type in which the input parameters are the rotational speeds of the low-pressure and high-pressure bodies, but also the temperature d 'turbine inlet, which leads to a very complex method or device of implementation where inter-actions are provided between these parameters and others such as the fuel flow rate or the nozzle opening section.
  • the operating laws adopted are also complex and must be translated by particular profiles of the connecting cam in the device.
  • the invention aims to reduce the number of parameters used and to define simple relationships between them which facilitate implementation.
  • Document FR-A-2 332 427 relates to a blockage warning detector and a blockage detection method for a turbomachine in which various parameters are also associated: turbine temperature (inlet or outlet), speed reduction speed of the compressor (high or low pressure), position of the compressor relief valves.
  • Document GB-A-1 492 924 relates to a fuel flow control device for a turbomachine in which the parameters chosen are a speed of rotation (possibly of high-pressure body) and another parameter increasing with speed but decreasing in case of rotary detachment which is the outlet pressure of the compressor.
  • GB-A-1 422 572 also relates to a control device using an electronic tachometer.
  • a comparator receiving two shaft speed signals is associated with a speed differentiator and a threshold switch, the output signals being supplied to an AND gate.
  • an object of the invention is to propose a method for investigating the operating parameters of a turbomachine, evolving before the appearance of rotary detachment, in a characteristic manner.
  • Another object of the invention consists in making a device capable of using the data coming from appropriate sensors, of processing them in a function generator, of discriminating if two conditions are met, and of triggering an alarm in the cockpit of the turbomachine.
  • the method according to the invention according to which the speed of rotation N HP , N BP of each of the rotating bodies is measured, is characterized in that the derivative with respect to time is deduced of the rotation speed N HP of the high pressure body and a control signal is generated as soon as we have: and where A, B and C are constant values.
  • control signal is used to trigger an alarm.
  • said control signal serves to trigger an operation making it possible to return to normal operating conditions of the turbomachine.
  • the detection device is due to type comprising a first detector measuring the speed of rotation (N HP ) of the high pressure body and a second detector measuring the speed of rotation (N BP ) of the low pressure body; this detection device is characterized in that it further comprises: a multiplier by a constant A, this multiplier receiving the signal (N BP ) emitted by the second detector; a subtractor subtracting from the signal (N HP ) emitted by the first detector, the signal (A - N BP ) supplied by the multiplier; a first comparator comparing the signal (Nnp ⁇ A ⁇ N BP ) supplied by the subtractor with a reference signal (B) supplied by a reference signal source; a derivative receiving the signal (N HP ) emitted by the first detector; a second comparator comparing the signal ( ) supplied by the diverter with a second reference signal (C) supplied by a second reference signal source, the first and second comparators each being of the type providing a logic signal "0" or "1
  • the gas turbine engine illustrated in FIG. 1 is a double flow axial flow motor comprising an engine casing 1 in which are mounted, as is known, a low pressure compressor 2 and its drive turbine 3 , as well as a high pressure compressor 4 and its drive turbine 5.
  • a combustion device 6 burns the fuel it receives from a command (not shown) by releasing drive gas from the turbines 3, 5, these gases then being evacuated by a nozzle in order to produce the thrust.
  • the parameters used are the rotational speeds of the high pressure and low pressure bodies.
  • the law for the correct adaptation of these regimes is established in the form:
  • a discriminating criterion eliminates the normal deceleration phases of the engine in the form of a test on the derivative of the rotation regime of the high pressure body with respect to time:
  • the device for detecting a rotating detachment shown in FIG. 2 comprises: a first detector 7 measuring the speed of rotation (N H p) of the high pressure body 4a, 5 and a second detector 8 measuring the speed of rotation (N BP ) of the low pressure body 2a, 3; a multiplier by a constant A, 9, this multiplier receive the signal (N BP ) emitted by the second detector 8; a subtractor 10 subtracting from signal (N HP ) emitted by the first detector 7, the signal (A ⁇ N) supplied by the multiplier 9, a first comparator 11 comparing the signal (NHP-A ⁇ N BP ) supplied by the subtractor 10 with a reference signal (B) provided by a reference signal source 12; a shunt 13 receiving the signal (N HP ) emitted by the first detector 7; a second comparator 14 comparing the signal ( ) supplied by the differentiator 13 with a second reference signal (C) supplied by a second reference signal source 15, the first 11 and second 14 comparators each
  • the logic circuit 11, 12, 14, 15, 16 causes the operation of an optical or audible alarm system (or both) 17 which warns the pilot that the engine is in revolving take-off.
  • the latter can then apply a setpoint making it possible to return to normal engine operating conditions.
  • the detection device 7 to 16 can optionally control the automatic execution of a maneuver making it possible to find these normal operating conditions (for example, programming a negative flow step) and a gradual return to the initial operating point.
  • the device shown in Figure 2 can use conventional electronic components; however, other elements, for example fluidics, can be used. It may be advantageous to use for the detection of N HP and N BP the detectors already existing in the regulator; alternatively, these detectors can also be specific to the device.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Testing Of Engines (AREA)
EP81401162A 1980-08-13 1981-07-22 Procédé et dispositif de détection de décollement tournant Expired EP0046698B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8018024A FR2488696A1 (fr) 1980-08-13 1980-08-13 Procede et dispositif de detection du decollement tournant apparaissant dans une turbomachine a deux corps tournants
FR8018024 1980-08-13

Publications (2)

Publication Number Publication Date
EP0046698A1 EP0046698A1 (fr) 1982-03-03
EP0046698B1 true EP0046698B1 (fr) 1984-03-14

Family

ID=9245222

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81401162A Expired EP0046698B1 (fr) 1980-08-13 1981-07-22 Procédé et dispositif de détection de décollement tournant

Country Status (5)

Country Link
US (1) US4430855A (enrdf_load_stackoverflow)
EP (1) EP0046698B1 (enrdf_load_stackoverflow)
JP (1) JPS5760246A (enrdf_load_stackoverflow)
DE (1) DE3162663D1 (enrdf_load_stackoverflow)
FR (1) FR2488696A1 (enrdf_load_stackoverflow)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4651518A (en) * 1984-12-18 1987-03-24 United Technologies Corporation Transient derivative scheduling control system
US4651563A (en) * 1985-10-16 1987-03-24 Sperry Corporation Jet engine testing apparatus
DE3540088A1 (de) * 1985-11-12 1987-05-14 Gutehoffnungshuette Man Verfahren zur erfassung von pumpstoessen an turbokompressoren
US4756152A (en) * 1986-12-08 1988-07-12 United Technologies Corporation Control for bleed modulation during engine deceleration
US5051918A (en) * 1989-09-15 1991-09-24 United Technologies Corporation Gas turbine stall/surge identification and recovery
US5402632A (en) * 1994-02-22 1995-04-04 Pratt & Whitney Canada, Inc. Method of surge detection
RU2109174C1 (ru) * 1996-01-05 1998-04-20 Акционерное общество "Авиадвигатель" Устройство для регулирования перепуска воздуха из компрессора газотурбинного двигателя самолета
KR100390862B1 (ko) * 2001-01-17 2003-07-10 한국과학기술연구원 터보압축기 불안정성 감지장치
US6557400B2 (en) 2001-03-30 2003-05-06 Honeywell International Inc. Surge bleed valve fault detection
FR2911972B1 (fr) * 2007-01-30 2009-03-27 Hispano Suiza Sa Procede de surveillance de moteurs d'avion
GB201121639D0 (en) 2011-12-16 2012-01-25 Rolls Royce Plc Shaft break detection
CN112901354B (zh) * 2021-02-01 2022-04-01 中国航发沈阳发动机研究所 一种航空发动机异常掉转故障处置对策方法
CN114151320B (zh) * 2021-10-20 2023-06-13 中国航发四川燃气涡轮研究院 一种压气机流动系统失稳的识别算法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2785848A (en) * 1953-08-28 1957-03-19 Rolls Royce Gas turbine engines with speed control mechanism
US2918790A (en) * 1955-11-25 1959-12-29 Grovar Inc Gas turbine power plant system
US3638422A (en) * 1970-06-26 1972-02-01 Gen Electric Two-shaft gas turbine control system
DE2200805A1 (de) * 1972-01-08 1973-07-19 Bosch Gmbh Robert Schaltungsanordnung zur ueberwachung eines elektronischen drehzahlmessers
US3854287A (en) * 1973-12-26 1974-12-17 United Aircraft Corp Self-trimming control for turbofan engines
US3971208A (en) * 1974-04-01 1976-07-27 The Garrett Corporation Gas turbine fuel control
GB1492924A (en) * 1974-11-06 1977-11-23 Lucas Industries Ltd Gas turbine engine fuel control system
US4117668A (en) * 1975-11-19 1978-10-03 United Technologies Corporation Stall detector for gas turbine engine
US4060980A (en) * 1975-11-19 1977-12-06 United Technologies Corporation Stall detector for a gas turbine engine
US4060979A (en) * 1975-11-19 1977-12-06 United Technologies Corporation Stall warning detector for gas turbine engine

Also Published As

Publication number Publication date
JPS5760246A (en) 1982-04-12
FR2488696B1 (enrdf_load_stackoverflow) 1983-12-09
US4430855A (en) 1984-02-14
JPH0117532B2 (enrdf_load_stackoverflow) 1989-03-30
FR2488696A1 (fr) 1982-02-19
EP0046698A1 (fr) 1982-03-03
DE3162663D1 (en) 1984-04-19

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