EP0046698A1 - Means and method for detecting rotating stall - Google Patents

Means and method for detecting rotating stall Download PDF

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Publication number
EP0046698A1
EP0046698A1 EP81401162A EP81401162A EP0046698A1 EP 0046698 A1 EP0046698 A1 EP 0046698A1 EP 81401162 A EP81401162 A EP 81401162A EP 81401162 A EP81401162 A EP 81401162A EP 0046698 A1 EP0046698 A1 EP 0046698A1
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Prior art keywords
signal
detector
comparator
supplied
rotation
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German (de)
French (fr)
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EP0046698B1 (en
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Pierre Edouard Deneux
Patrick Jean Faure
Denis René Guy Laffitte
Michel Eugène Marcel Lemaoult
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • 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 FIG. 1 is an example of the different types of engines for which the present invention can be used.
  • 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 gases driving the turbines 3, 5, these gases then being evacuated by a nozzle in order to produce the thrust.
  • the invention also relates to a rotating detachment detection device.
  • these parameters T, N HP , N BP stabilize at values different from those corresponding to normal stabilization, but, under certain conditions, serious accidents can occur suddenly: extinction at the level of the combustion device 6, rupture of blades, etc.
  • an object of the invention is to propose a method for investigating operating parameters. of a turbomachine, evolving before the appearance of the rotary detachment, in a characteristic manner.
  • Another object of the invention consists in proposing the use of a law of constant evolution for several pairs of parameters, cet.loi being characteristic of the appearance of separation.
  • a third 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 is characterized in that the derivative with respect to time dN HP is deduced from the speed of rotation N H p of the high pressure body and we generate a control signal 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 of the 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 B p) 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 H p) emitted by the first detector, the signal (A. N B p) supplied by the multiplier; a first comparator comparing the signal (N HP - A.
  • N BP N BP supplied by the subtractor with a reference signal (B) supplied by a reference signal source; a derivative receiving the signal (N H p) emitted by the first detector; a second comparator comparing the signal ( dN HP) 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 "depending on whether the reference signal received by this. comparator is greater or less than the other signal applied to this comparator; and an AND gate with two inputs each receiving the output signal from a respective comparator, and the output of which delivers a control signal.
  • 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:
  • N HP and -N HP being expressed in% of the nominal speeds of the high pressure and low pressure bodies and the time dt expressed in seconds:
  • the device for detecting a rotary detachment shown in FIG. 2 comprises: a first detector 7 measuring the speed of rotation (NHP) of the high pressure body 4a, 5 and a second detector 8 measuring the speed of rotation (NBP) of the body low pressure 2a, 3; a multiplier by a constant A, 9, this multiplier receiving the signal (NBP) emitted by the second detector 8; a subtractor 10 subtracting from the signal (N HP ) emitted by the first detector 7, the signal (AN) supplied by the multiplier 9, a first comparator 11 comparing the signal (N HP - AN B p) supplied by the subtractor 10 with a reference signal (B) supplied 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 ( dN HP) 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 being of the type providing
  • 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 running. 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 command the automatic execution of a maneuver enabling these normal operating conditions to be restored (for example, programming of 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 EP the detectors already existing in the regulator; alternatively, these detectors can also be specific to the device.

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  • 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)

Abstract

Dans une turbomachine ayant deux corps tournants : un corps haute pression et un corps basse pression, on mesure, au moyen de détecteurs (7, 8) la vitesse de rotation (NHP, NBP) de chacun desdits corps, on déduit (dérivateur 13) la dérivée par rapport au temps dNHP/dt de la vitesse de rotation NHP du corps haute pression et on génère un signal de commande dès que l'on a : <IMAGE> où A, B et C sont des valeurs constantes.In a turbomachine having two rotating bodies: a high pressure body and a low pressure body, the speed of rotation (NHP, NBP) of each of said bodies is measured by means of detectors (7, 8), we deduce (shunt 13) the derivative with respect to time dNHP / dt of the speed of rotation NHP of the high pressure body and a control signal is generated as soon as we have: <IMAGE> where A, B and C are constant values.

Description

La présente invention concerne un procédé de détection d'un décollement tournant dans une turbomachine ayant deux corps tournants : un corps haute pression et un corps basse pression, procédé du type selon lequel on mesure la vitesse de rotation de chacun desdits corps.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.

Le moteur à turbine à gaz illustré en figure 1 est un exemple des différents types de moteurs pour lesquels la présente invention peut être utilisée..The gas turbine engine illustrated in FIG. 1 is an example of the different types of engines for which the present invention can be used.

Le moteur à turbine à gaz illustré en figure 1 est un moteur à débit axial double flux comportant une enveloppe de moteur 1 dans laquelle sont montés, de manière rotative, comme il est connu, un compresseur basse pression 2 et sa turbine d'entraînement 3, ainsi qu'un compresseur haute pression 4 et sa turbine d'entraînement 5. Un dispositif de combustion 6 brûle le carburant qu'il reçoit d'une commande (non représentée) en dégageant des gaz entraînant les turbines 3, 5, ces gaz étant ensuite évacués par une tuyère afin de produire la poussée.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 gases driving the turbines 3, 5, these gases then being evacuated by a nozzle in order to produce the thrust.

L'invention concerne aussi un dispositif de détection de décollement tournant.The invention also relates to a rotating detachment detection device.

Le décollement tournant est un phénomène qui affecte toutes les turbomachines à divers régimes de fonctionnement. Si les causes en sont encore mal connues, les effets sur les moteurs double-corps se manifestent presque toujours de la même manière :

  • - chute brutale de la pression de sortie du compresseur 2, 4 suivie d'une croissance de cette pression inférieure au taux de croissance normal ;
  • - augmentation brutale de la température T du flux de gaz à l'entrée des turbines 5, 3, se tradui- . sant parfois par une cassure dans la pente de la courbe.de cette température en fonction du temps, et une stabilisation de cette température à des niveaux plus élevés que le niveau normal de consigne ;
  • - une croissance du régime de rotation NHp du corps haute pression 4a, 5 inférieure au taux de croissance normal ;
  • - une stabilisation instantanée du régime de rotation NHp du corps basse pression 2a, 3, suivie d'une croissance faible de ce régime NBP ;
  • - parfois des grondements et une inversion de fonctionnement dite "pompage" du compresseur 2, 4.
Rotary detachment is a phenomenon that affects all turbomachinery at various operating speeds. If the causes are still poorly understood, the effects on double-barrel motors almost always manifest themselves in the same way:
  • - sudden drop in the outlet pressure of compressor 2, 4 followed by a growth in this pressure lower than normal growth rate;
  • - sudden increase in the temperature T of the gas flow at the inlet of the turbines 5, 3, results. sometimes by a break in the slope of the curve. of this temperature as a function of time, and a stabilization of this temperature at levels higher than the normal setpoint level;
  • a growth of the rotation regime N H p of the high pressure body 4a, 5 lower than the normal growth rate;
  • an instantaneous stabilization of the rotation regime N Hp of the low pressure body 2a, 3, followed by a weak growth of this regime N BP ;
  • - sometimes rumblings and an inversion of operation called "pumping" of the compressor 2, 4.

Au bout d'un intervalle de temps de plusieurs secondes, ces paramètres T, NHP, NBP se stabilisent à des valeurs différentes de celles correspondant à une stabilisation normale, mais, dans certaines conditions des accidents graves peuvent survenir brutalement : extinction au niveau du dispositif de combustion 6, rupture d'aubes, etc...At the end of a time interval of several seconds, these parameters T, N HP , N BP stabilize at values different from those corresponding to normal stabilization, but, under certain conditions, serious accidents can occur suddenly: extinction at the level of the combustion device 6, rupture of blades, etc.

Il importe donc que le pilote ou autre utilisateur soit informé rapidement de l'apparition du décollement tournant ou de l'imminence de son déclenchement afin de pouvoir prendre à temps les mesures propres à le prévenir.It is therefore important that the pilot or other user be promptly informed of the appearance of the revolving take-off or of the imminence of its triggering in order to be able to take timely measures to prevent it.

C'est pourquoi un objet de l'invention est de proposer un procédé d'investigation de paramètres de fonctionnement d'une turbomachine, évoluant avant l'apparition du décollement tournant, d'une manière caractéristique.This is why an object of the invention is to propose a method for investigating operating parameters. of a turbomachine, evolving before the appearance of the rotary detachment, in a characteristic manner.

Un autre objet de l'invention consiste à proposer l'utilisation d'une loi d'évolution constante pour plusieurs couples de paramètres, cette.loi étant caractéristique de l'apparition du décollement.Another object of the invention consists in proposing the use of a law of constant evolution for several pairs of parameters, cet.loi being characteristic of the appearance of separation.

Un troisième objet de l'invention consiste à réaliser un dispositif capable d'utiliser les données en provenance de capteurs appropriés, de les traiter dans un générateur de fonctions, de discriminer si deux conditions sont réunies, et de déclencher une alarme au poste de pilotage de la turbomachine.A third 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.

A ces effets, le procédé conforme à l'invention, selon lequel on mesure la vitesse de rotation NHP, NBp de chacun des corps tournants, est caractérisé en ce qu'on déduit la dérivée par rapport au temps dNHP de la vitesse de rotation NHp du corps haute pression et on génère un signal de commande dès que l'on a

Figure imgb0001
Figure imgb0002
et où A, B et C sont des valeurs constantes.For these effects, 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 dN HP is deduced from the speed of rotation N H p of the high pressure body and we generate a control signal as soon as we have
Figure imgb0001
Figure imgb0002
 and where A, B and C are constant values.

C'est ainsi que, dans une application particulière de l'invention à un moteur connu, on détermine les valeurs suivantes, lorsque les vitesses de rotation interviennent en % de la valeur nominale :

  • A est compris entre 1 et 1,5, B est compris entre
  • 8 et 30, C est compris entre - 0,6 et - 0, 2 et dans un cas particulier, A est égal à 1,26 ; B est égal à 18,2 et C est égal à - 0,4.
Thus, in a particular application of the invention to a known motor, the following values are determined, when the rotational speeds occur as a% of the nominal value:
  • A is between 1 and 1.5, B is between
  • 8 and 30, C is between - 0.6 and - 0, 2 and in a particular case, A is equal to 1.26; B is 18.2 and C is - 0.4.

Lorsque les vitesses de rotation interviennent en valeur absolue, on choisit A égal à 1,62 ; B égal à 4106 tours/mn et C égal à - 250 tours/mn/s.When the speeds of rotation intervene in absolute value, we choose A equal to 1.62; B equal to 4106 rpm and C equal to - 250 rpm.

Par exemple, ledit signal de commande sert à déclencher une alarme.For example, said control signal is used to trigger an alarm.

Alternativement ou simultanément, selon un aspect de l'invention, ledit signal de commande sert à déclencher une manoeuvre permettant de revenir à des conditions normales de fonctionnement de la turbomachine.Alternatively or simultaneously, according to one aspect of the invention, said control signal serves to trigger an operation making it possible to return to normal operating conditions of the turbomachine.

Le dispositif de détection conforme à l'invention est du type comprenant un premier détecteur mesurant la vitesse de rotation (NHP) du corps haute pression et un second détecteur mesurant la vitesse de rotation (NBp) du corps basse pression ; ce dispositif de détection est caractérisé en ce qu'il comporte en outre : un multiplicateur par une constante A, ce multiplicateur recevant le signal (NBP) émis par le second détecteur ; un soustracteur soustrayant du signal (NHp) émis par le premier détecteur, le signal (A . NBp) fourni par le multiplicateur ; un premier comparateur comparant le signal (NHP - A . NBP) fourni par le soustracteur avec un signal de référence (B) fourni par une source de signal de référence ; un dérivateur recevant le signal (NHp) émis par le premier détecteur ; un deuxième comparateur comparant le signal (dNHP) fourni par le déri- vateur avec un deuxième signal de référence (C) fourni par une deuxième source de signal de référence, les premier et second comparateurs étant chacun du type fournissant un signal logique "0" ou "1" selon que le signal de référence reçu par ce. comparateur est supérieur ou inférieur à l'autre signal appliqué à ce comparateur ; et une porte ET à deux entrées recevant chacune le signal de sortie d'un comparateur respectif, et dont la sortie délivre un signal de commande.The detection device according to the invention is of the 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 B p) 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 H p) emitted by the first detector, the signal (A. N B p) supplied by the multiplier; a first comparator comparing the signal (N HP - A. N BP ) supplied by the subtractor with a reference signal (B) supplied by a reference signal source; a derivative receiving the signal (N H p) emitted by the first detector; a second comparator comparing the signal ( dN HP) 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 "depending on whether the reference signal received by this. comparator is greater or less than the other signal applied to this comparator; and an AND gate with two inputs each receiving the output signal from a respective comparator, and the output of which delivers a control signal.

Les caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'un mode de réalisation de l'invention, description faite en référence aux dessins annexés dans lesquels :

  • - la figure 1, déjà décrite, est une coupe axiale schématique à travers un moteur à turbine à gaz double flux ; et
  • - la figure 2 est un schéma synoptique d'un dispo- sitif de détection selon un mode de réalisation de l'invention.
The characteristics and advantages of the invention will be better understood on reading the description which follows of an embodiment of the invention, description made with reference to the accompanying drawings in which:
  • - Figure 1, already described, is a schematic axial section through a double flow gas turbine engine; and
  • - Figure 2 is a block diagram of an available - detecting operative part according to one embodiment of the invention.

Ainsi, selon l'invention, les paramètres utilisés sont les vitesses de rotation des corps haute pression et basse pression. La loi d'adaptation correcte de ces régimes est établie sous la forme :

Figure imgb0003
Thus, according to the invention, 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:
Figure imgb0003

Un critère discriminateur élimine les phases de décélération normale du moteur sous la forme d'un test sur la dérivée du régime de rotation du corps haute pression par rapport au temps :

Figure imgb0004
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:
Figure imgb0004

Un cas particulier d'application de ce procédé donne les valeurs suivantes, les valeurs de NHP et-NHP étant exprimées en % des régimes nominaux des corps haute pression et basse pression et le temps dt exprimé en secondes :

Figure imgb0005
A particular case of application of this method gives the following values, the values of N HP and -N HP being expressed in% of the nominal speeds of the high pressure and low pressure bodies and the time dt expressed in seconds:
Figure imgb0005

Lorsque N HP et NBP sont exprimés en tours par minute et le temps dt en secondes, on choisit :

Figure imgb0006
When N HP and N BP are expressed in revolutions per minute and the time dt in seconds, we choose:
Figure imgb0006

Ce procédé de détection présente de nombreux avantages :

  • - les paramètres NHP et NBP sont obtenus avec une grande précision et présentent une dispersion faiblé ;
  • - les conditions ISA (International Standard Atmosphère) ont une faible influence sur ces paramètres ;
  • - le temps maximal de détection est de l'ordre de 3 secondes ;
  • - ces paramètres nécessaires à la détection sont déjà utilisés pour la régulation normale.
This detection method has many advantages:
  • - the parameters N HP and N BP are obtained with great precision and have a weak dispersion;
  • - ISA (International Standard Atmosphere) conditions have little influence on these parameters;
  • - the maximum detection time is around 3 seconds;
  • - these parameters necessary for detection are already used for normal regulation.

Le dispositif de détection d'un décollement tournant représenté à la figure 2 comprend : un premier détecteur 7 mesurant la vitesse de rotation (NHP) du corps haute pression 4a, 5 et un second détecteur 8 mesurant la vitesse de rotation (NBP) du corps basse pression 2a, 3 ; un multiplicateur par une constante A, 9, ce multiplicateur recevant le signal (NBP) émis par le second détecteur 8 ; un soustracteur 10 soustrayant du signal (NHP) émis par le premier détecteur 7, le signal (A.N) fourni par le multiplicateur 9, un premier comparateur 11 comparant le signal (NHP - A.NBp) fourni par le soustracteur 10 avec un signal de référence (B) fourni par une source de signal de référence 12; un dérivateur 13 recevant le signal (NHP) émis par le premier détecteur 7 ; un deuxième comparateur 14 comparant le signal (dNHP) fourni par le dérivateur 13 avec un deuxième signal de référence (C) fourni par une deuxième source de signal de référence 15, les premier 11 et second 14 comparateurs étant chacun du type fournissant un signal logique "D" ou "1" selon que le signal de référence reçu par ce comparateur est, respectivement, inférieur ou supérieur à l'autre signal appliqué à ce comparateur ; et une porte ET, 16. à deux entrées 16a, 16b recevant chacune le signal de sortie d'un comparateur respectif 11, 14.The device for detecting a rotary detachment shown in FIG. 2 comprises: a first detector 7 measuring the speed of rotation (NHP) of the high pressure body 4a, 5 and a second detector 8 measuring the speed of rotation (NBP) of the body low pressure 2a, 3; a multiplier by a constant A, 9, this multiplier receiving the signal (NBP) emitted by the second detector 8; a subtractor 10 subtracting from the signal (N HP ) emitted by the first detector 7, the signal (AN) supplied by the multiplier 9, a first comparator 11 comparing the signal (N HP - AN B p) supplied by the subtractor 10 with a reference signal (B) supplied 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 ( dN HP) 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 being of the type providing a signal logic "D" or "1" depending on whether the reference signal received by this comparator is, respectively, lower or higher than the other signal applied to this comparator; and an AND gate, 16. with two inputs 16a, 16b each receiving the output signal from a respective comparator 11, 14.

A partir des détecteurs de régime HP et BP 7 et 8, les divers générateurs de fonction 9, 10 et 13 Calculent les valeurs de NHP - A.NBP et dNHP dtFrom the HP and BP speed detectors 7 and 8, the various function generators 9, 10 and 13 Calculate the values of N HP - AN BP and dN HP dt

Lorsque les deux conditions

Figure imgb0007
sont réunies, le circuit logique 11, 12, 14, 15, 16 entraîne le fonctionnement d'un.système d'alarme optique ou sonore (ou les deux) 17 qui prévient le pilote que le moteur est en décollement tournant. Celui-ci peut alors appliquer une consigne permettant de revenir à des conditions normales de fonctionnement du moteur.When the two conditions
Figure imgb0007
 are combined, 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 running. The latter can then apply a setpoint making it possible to return to normal engine operating conditions.

Le dispositif de détection 7 à 16 peut éventuellement commander l'exécution automatique d'une manoeuvre permettant de retrouver ces conditions normales du fonctionnement (par exemple, programmation d'un échelon de débit négatif) et un retour progressif au point de fonctionnement initial .The detection device 7 to 16 can optionally command the automatic execution of a maneuver enabling these normal operating conditions to be restored (for example, programming of a negative flow step) and a gradual return to the initial operating point.

Le dispositif représenté sur la figure 2 peut utiliser des composants électroniques classiques ; cependant d'autres éléments, par exemple fluidiques, sont utilisables. Il peut être avantageux d'utiliser pour la détection de NHP et NEP les détecteurs existant déjà dans le régulateur ; alternativement, ces détecteurs peuvent également être particuliers au dispositif.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 EP the detectors already existing in the regulator; alternatively, these detectors can also be specific to the device.

Claims (7)

1. Procédé de détection d'un décollement tournant dans une turbomachine'ayant deux corps tournants : un corps haute pression (4a, 5) et un corps basse pression (2a, 3), du type selon lequel on mesure la vitesse de rotation (NHP,NHP) de chacun desdits corps, caractérisé en ce qu'on déduit la dérivée par rapport au temps
Figure imgb0008
 de la vitesse de rotation NHP du corps haute pression et on génère un signal de commande dès que l'on a :
Figure imgb0009
et
Figure imgb0010
où A, B et C sont des valeurs constantes.1. Method for detecting a rotating detachment in a turbomachine having two rotating bodies: a high pressure body (4a, 5) and a low pressure body (2a, 3), of the type according to which the speed of rotation is measured ( N HP , N HP ) of each of said bodies, characterized in that the derivative with respect to time is deduced
Figure imgb0008
 of the rotation speed N HP of the high pressure body and a control signal is generated as soon as we have:
Figure imgb0009
 and
Figure imgb0010
 where A, B and C are constant values. 2. Procédé selon la revendication 1, caractérisé en ce que, lorsque les vitesses de rotation interviennent en % de la valeur nominale, les coefficients sont calculés en conséquence et A est compris entre 1 et 1,5, B est compris entre 8 et 30 et C est compris entre - 0,6 et - 0,2.2. Method according to claim 1, characterized in that, when the rotational speeds occur as a% of the nominal value, the coefficients are calculated accordingly and A is between 1 and 1.5, B is between 8 and 30 and C is between - 0.6 and - 0.2. 3. Procédé selon la revendication 2, caractérisé en ce que, sensiblement, A est égal à 1,26 ; B est égal à 18,2 et C à - 0,4.3. Method according to claim 2, characterized in that, substantially, A is equal to 1.26; B is 18.2 and C is -0.4. 4. Procédé selon la revendication 1, caractérisé en ce que, lorsque les vitesses de rotation interviennent en valeur absolue, les coefficients sont calculés en conséquence et, sensiblement A est égal à 1,62 ; B est égal à 4106 tours/mn et C est égal à - 250 tours/mn/s.4. Method according to claim 1, characterized in that, when the rotational speeds occur in absolute value, the coefficients are calculated accordingly and, substantially A is equal to 1.62; B is equal to 4106 rpm and C is - 250 rpm. 5. Procédé selon l'une des revendications précédentes, caractérisé en ce que ledit signal de commande sert à déclencher une alarme.5. Method according to one of the preceding claims, characterized in that said control signal is used to trigger an alarm. 6. Procédé selon l'une des revendications précédentes, caractérisé en ce que ledit signal de commande sert à déclencher une manoeuvre permettant de revenir à des conditions normales de fonctionnement de la turbomachine.6. Method according to one of the preceding claims, characterized in that said control signal serves to trigger an operation making it possible to return to normal operating conditions of the turbomachine. 7. Dispositif de détection d'un décollement tournant dans une turbomachine comportant un corps tournant haute pression (4a, 5) et un corps tournant basse pression (2a, 3), du type comprenant un premier détecteur (7) mesurant la vitesse de rotation (NHP) du corps haute pression et unsecond détecteur (8) mesurant la vitesse de rotation (NBP) du corps basse pression, caractérisé en ce qu'il comporte en outre : un multiplicateur par une constante A, (9), ce multiplicateur recevant le signal (NBP) émis par le.second détecteur (8) ; un soustracteur (10) soustrayant du signal (NHP) émis par le premier détecteur (7), le signal (A.NBP) fourni par le multiplicateur (9) ; un premier comparateur (11) comparant le signal (NHP - A.NBP) fourni par le soustracteur (10) avec un signal de référence (B) fourni par une première source de signal de référence (12) ; un dérivateur (13) recevant le signal (NHP) émis par le premier détecteur (7) ; un deuxième comparateur (14) comparant le signal (dNHP) fourni par le dérivateur (13) avec un deuxième signal de référence (C) fourni par une deuxième source de signal de référence (15), les premier (11) et second (14) comparateurs étant chacun du type fournissant un signal logique "0" et "1" selon que le signal de référence reçu par ce comparateur est inférieur ou supérieu.r à l'autre signal appliqué à ce comparateur ; et une porte ET, (16) à deux entrées (16a, 16b) recevant chacune le signal de sortie d'un comparateur respectif (11,'14), et dont la sortie délivre un signal de commande.7. Device for detecting a rotating detachment in a turbomachine comprising a high pressure rotating body (4a, 5) and a low pressure rotating body (2a, 3), of the type comprising a first detector (7) measuring the speed of rotation (N HP ) of the high pressure body and a second detector (8) measuring the speed of rotation (N BP ) of the low pressure body, characterized in that it further comprises: a multiplier by a constant A, (9), this multiplier receiving the signal (N BP ) emitted by the second detector (8); a subtractor (10) subtracting from the signal (N HP ) emitted by the first detector (7), the signal (AN BP ) supplied by the multiplier (9); a first comparator (11) comparing the signal (N HP - AN BP ) supplied by the subtractor (10) with a reference signal (B) supplied by a first 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 ( dN HP) 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 being of the type providing a logic signal "0" and "1" depending on whether the reference signal received by this comparator is less than or greater than the other signal applied to this comparator; and an AND gate, (16) with two inputs (16a, 16b) each receiving the output signal from a respective comparator (11, '14), and the output of which delivers a control signal.
EP81401162A 1980-08-13 1981-07-22 Means and method for detecting rotating stall Expired EP0046698B1 (en)

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FR8018024 1980-08-13
FR8018024A FR2488696A1 (en) 1980-08-13 1980-08-13 METHOD AND APPARATUS FOR DETECTING ROTATING FLASHING APPEARING IN A TURBOMACHINE WITH TWO ROTATING BODIES

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EP0046698A1 true EP0046698A1 (en) 1982-03-03
EP0046698B1 EP0046698B1 (en) 1984-03-14

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0222383A2 (en) * 1985-11-12 1987-05-20 MAN Gutehoffnungshütte Aktiengesellschaft Process for recording pump surges in turbo compressors
EP0418189A2 (en) * 1989-09-15 1991-03-20 United Technologies Corporation Gas turbine stall/surge identification and recovery

Families Citing this family (10)

* 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
US4756152A (en) * 1986-12-08 1988-07-12 United Technologies Corporation Control for bleed modulation during engine deceleration
US5402632A (en) * 1994-02-22 1995-04-04 Pratt & Whitney Canada, Inc. Method of surge detection
KR100390862B1 (en) * 2001-01-17 2003-07-10 한국과학기술연구원 Instability detector of turbo compressor
US6557400B2 (en) 2001-03-30 2003-05-06 Honeywell International Inc. Surge bleed valve fault detection
FR2911972B1 (en) * 2007-01-30 2009-03-27 Hispano Suiza Sa METHOD FOR MONITORING AIRCRAFT ENGINES
GB201121639D0 (en) 2011-12-16 2012-01-25 Rolls Royce Plc Shaft break detection
CN112901354B (en) * 2021-02-01 2022-04-01 中国航发沈阳发动机研究所 Countermeasure method for handling abnormal rotation-dropping fault of aircraft engine
CN114151320B (en) * 2021-10-20 2023-06-13 中国航发四川燃气涡轮研究院 Identification algorithm for instability of compressor flow system

Citations (6)

* 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
GB1422572A (en) * 1972-01-08 1976-01-28 Bosch Gmbh Robert Speed sensitive control arrangements
FR2332427A1 (en) * 1975-11-19 1977-06-17 United Technologies Corp BLOCKING WARNING DETECTOR AND BLOCKING DETECTION METHOD IN A GAS TURBINE ENGINE
GB1492924A (en) * 1974-11-06 1977-11-23 Lucas Industries Ltd Gas turbine engine fuel control system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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

Patent Citations (6)

* 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
GB1422572A (en) * 1972-01-08 1976-01-28 Bosch Gmbh Robert Speed sensitive control arrangements
GB1492924A (en) * 1974-11-06 1977-11-23 Lucas Industries Ltd Gas turbine engine fuel control system
FR2332427A1 (en) * 1975-11-19 1977-06-17 United Technologies Corp BLOCKING WARNING DETECTOR AND BLOCKING DETECTION METHOD IN A GAS TURBINE ENGINE

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0222383A2 (en) * 1985-11-12 1987-05-20 MAN Gutehoffnungshütte Aktiengesellschaft Process for recording pump surges in turbo compressors
EP0222383A3 (en) * 1985-11-12 1988-01-13 Man Gutehoffnungshutte Gmbh Process for recording pump surges in turbo compressors
EP0418189A2 (en) * 1989-09-15 1991-03-20 United Technologies Corporation Gas turbine stall/surge identification and recovery
EP0418189A3 (en) * 1989-09-15 1991-11-21 United Technologies Corporation Gas turbine stall/surge identification and recovery

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EP0046698B1 (en) 1984-03-14
DE3162663D1 (en) 1984-04-19
JPS5760246A (en) 1982-04-12
JPH0117532B2 (en) 1989-03-30
FR2488696A1 (en) 1982-02-19
FR2488696B1 (en) 1983-12-09
US4430855A (en) 1984-02-14

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