CA1071435A - Stall warning detector for gas turbine engine - Google Patents
Stall warning detector for gas turbine engineInfo
- Publication number
- CA1071435A CA1071435A CA264,759A CA264759A CA1071435A CA 1071435 A CA1071435 A CA 1071435A CA 264759 A CA264759 A CA 264759A CA 1071435 A CA1071435 A CA 1071435A
- Authority
- CA
- Canada
- Prior art keywords
- stall
- compressor
- turbine
- signal
- temperature
- 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
Links
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- 238000000034 method Methods 0.000 claims description 6
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- 238000012544 monitoring process Methods 0.000 abstract description 6
- 238000001514 detection method Methods 0.000 abstract description 4
- 230000007423 decrease Effects 0.000 abstract description 2
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 abstract 1
- 239000000446 fuel Substances 0.000 description 13
- 239000007789 gas Substances 0.000 description 11
- 230000008859 change Effects 0.000 description 6
- 230000003247 decreasing effect Effects 0.000 description 3
- 102100029469 WD repeat and HMG-box DNA-binding protein 1 Human genes 0.000 description 2
- 101710097421 WD repeat and HMG-box DNA-binding protein 1 Proteins 0.000 description 2
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- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
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Classifications
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
Abstract
STALL WARNING DETECTOR FOR
GAS TURBINE ENGINE
Abstract of the Disclosure A stall detector for a gas turbine engine is disclosed where detection is obtained by continously monitoring turbine temperature and either compressor speed or bleed valve position and provide a stall signal solely when turbine temperature exceeds a predetermined value and the compressor speed decreases at a predetermined rate or when turbine temperature exceeds a predetermined value at the time that the compressor bleeds are in the opened position.
GAS TURBINE ENGINE
Abstract of the Disclosure A stall detector for a gas turbine engine is disclosed where detection is obtained by continously monitoring turbine temperature and either compressor speed or bleed valve position and provide a stall signal solely when turbine temperature exceeds a predetermined value and the compressor speed decreases at a predetermined rate or when turbine temperature exceeds a predetermined value at the time that the compressor bleeds are in the opened position.
Description
~ ~ BACKGROUND OF THE _NVENTION
This invention relates to means for detecting stall in a gas turbine engine and more particularly to a stall detection system that continuously monitors two engine operating parameters and when prede~ermined conditions of both are met will produce an output signal indica~ive of stall.
As is well known, sta~l is a phenomenon that may occur in the compressor of a gas turbine engine which, if allowed to persist unabated~ would impair engine performance and/or lead to the destruction of the engine. While the theory of stall is not completely understood, suffice it to say that stall is that effect occasioned when sufficient number of - compressor blades stall and a momentary reversing of the airflow occurs through the compressor. This causes compressor ~`~
discharge pressure to drop very rapidly and sometimes results in continual pressure oscillations until ~ome corrective action is taken.
The art has seen a number of methods intended to either - sense when stall is imminent and warn the pilot so that he can take corrective action or design the engine controls such that the area of engine operation where stall is likely ~o occur is avoided.
For example, fuel controls limit the amount of fuel admitted to the engine during acceleration so as to accelerate along a predetermined acceleration schedule that accoun~s for stall. ~nother method, which may be contemporaneously
This invention relates to means for detecting stall in a gas turbine engine and more particularly to a stall detection system that continuously monitors two engine operating parameters and when prede~ermined conditions of both are met will produce an output signal indica~ive of stall.
As is well known, sta~l is a phenomenon that may occur in the compressor of a gas turbine engine which, if allowed to persist unabated~ would impair engine performance and/or lead to the destruction of the engine. While the theory of stall is not completely understood, suffice it to say that stall is that effect occasioned when sufficient number of - compressor blades stall and a momentary reversing of the airflow occurs through the compressor. This causes compressor ~`~
discharge pressure to drop very rapidly and sometimes results in continual pressure oscillations until ~ome corrective action is taken.
The art has seen a number of methods intended to either - sense when stall is imminent and warn the pilot so that he can take corrective action or design the engine controls such that the area of engine operation where stall is likely ~o occur is avoided.
For example, fuel controls limit the amount of fuel admitted to the engine during acceleration so as to accelerate along a predetermined acceleration schedule that accoun~s for stall. ~nother method, which may be contemporaneously
-2- ~
~7~L~3~ ~
employed with this accelera~ion scheduling system, is to measure compressor discharge pressure and open compressor bleed valves whenever a predetermined compressor pressure change or rate of change occurs. And still another method ;~
which is described in U.S. Patent No. 3,867,717 and granted to John Theodore Moehring and Vigil Willis Lawson on February 18, 1975 is the utillzation of computed compressor pressures and turbine or exit temperatures as a means for determining when stall is present.
While such stall detection and prevention means as described above may be effective for cer~ain engines and/or their applications they are not always effective for other engines and/or their applications. For example, it may happen that under the same values of the comp~ted compressor pressures or their rates and turbine ~emperatures or their rates another engine operation may occur which would lead to a false indication o~ stall; or the monitoring of the parameter may not be readily accessible or the inclusion of the se~sing probes may interfere with the gas path and impair engine performance. ThereforP the selection of the stall controller comes down to what stall system is best for that engine and its applica~ions, what parameters are readily accessible, which system will provide the highest degree of accuracy, which one is fastest and a host of other considera-tions.
, ~7:L~35 This invention contemplates continuously monitoring two engine operating parameters and when both are at predetermined valuel the stall warning detector will produce an output signal.
Th~ output signal can then be utilized to provide a warning signal to the aircraft pilot, as by a visual or sound signal so that he can take corrective action, such as retarding the power lever. Additionally, this signal can be utilized to initiate corrective action in one of the following ways:
1. de-rich engine fuel flow 2. shutoff fuel open compressor bleeds 4. change compressor stator vane angle 5. change aircraft inlet geome~ry 6. change engine outlet geometry Furthermore the signal can be incorporated in a system that would initiate an automatic stall recovery sequen~e by shutting-ofE fuel, start ignition and reinitiate fuel flow in a timed sequence.
We have found that the turbine inlet temperature (TIT) or turbin~ exit temperature (TET) are viable parameters for indicating stall if these values are excessively high (or abnormally so) and that the speed of the compressor (either low compressor (Nl) or high compressor (N2) in a twin spool .
~C97~35 engine) is decreasing or not increasing. Also in engines that utilize compressor bleed valves and particularly the ones that are opened as a function of compressor pressure ratio, the temperature signal together with a bleed position signal can be utilized as an indication of stall or imminent stallO
In both situations, this invention contemplates continuously monitoring the turbine temperature and either compressor speed or compressor bleed valve position and apply computed values of these parameters to an l'AND1' gate to obtain an output signal indicative of stall solely when TIT or TET is excessively high and the bleeds are opened or when TIT or TET is excessively high and Nl or N2 is rapidly decreasing.
SUMMARY OF THE INVENTION
An object of this invention is to provide an improved stall warning system for an axial flow gas turbine engine.
A still further object of this invention is to provide a stall warning system that utilizes either TIT or TET
together with ano~her engine operating parameter solely when predetermined conditions of each signal is satisfied.
A still further object of this invention is to provide a stall warning system that produces an output signal solely when both TIT or TET are excessively high and the engine bleeds are opened~
~7~
A still further object of this invention is to provide a stall warning system that produces an output signal solely when TIT or TET is excessively high and Nl or N2 is at a predetenmined rate of decreasing speed.
In accordance with an embodiment of the invention, a stall detector system for an axial flow gas turbine engine has a compressor, a turbine and burner, bleed valve means for bleeding air from said compressor, means for detecting when stall is imminent including a temperature sensor measuring the temperature of the turbine, comparator means for producing a first signal whenever the measured temperature exceeds a referenced value, signal generator means responsive to the position of said bleed valve means for producing a second signal whenever the bleed valve means is open to bleed said compressor, and gate means responsive to both said first sig-nal and said second signal for producing a stall warning out-put signal whenever both the temperature of said turbine is abnormally high and said bleed valve means is bleeding air from said compressorO
From a differen~ aspect, and in accordance with the invention, the method of detecting stall in flow.g~s turbine engine that includes a compressor~ turbine and burner and compressor bleed vlaves comprises the steps of: measuring the temperature in proximity to the turbine so as to produce an output signal whenever this temperature is excessive in relation to normal engine operation, measuring the position of the compressor bleed valves so as to produce an output signal whenever the compressor bleed valves are opened, combining the outputs obtained in the steps of measuring so as to produce a signal indicative of stall solely when both output;signals are present which signal can then be used as a warning or to initiate corrective action.
~ - 6 -~L~7~35 Other features ~nd advantages will be apparent rom the specification and claims and from the accompanying draw-ings which illustrate an embodiment of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a schematic representation, partially in section of a gas turbine engine, and a schematic represen-tation of a stall warning system connected thereto.
Fig. 2 is a schematic representation of another embodiment of a stall warning system connected to a typical gas turbine engine.
DESCRIPTION OF THE PREFERRED EMBODIMENT
For the purpose of this description, the gas turbine engine illustrated in Fig. 1 typifies any number of different types of engines where this invention may be utilized. Such engines may include, as for example, the JT-3D, JT-8D, JT- ;
9D, TF-30, ~T-12 manufactured by the Pratt & W~litney Aircraft Division of United Technologies Corporation, but are not limited thereto. Suffice it to say that this invention is applicable where stall is a problem which is generally the case in any axial flow compressor.
- 6a -.~
`~D , ,. . :
~ 3 ~
Es6entially, the gas turbine engine exemplified by Fig, 1 is a twin spool a~ial flow gas turbine engine having an engine casing 10 in which the low pressure compressor 12 and driving turbine 14 and high pressure compressor 16 and its driving turbine 18 are rotary mounted. The burner section 20 which burns fuel metered thereto by fuel control (not shown) generates gases for driving the turbines which then are exhausted through a nozzle to produce thrust or the thrust is augmented by a suitable af~erburner 24. :~
Depending on the particular engine and its application it may include a variable geometry inlet duct 32, variable compressor stators generally illustrated by referen~e numeral 34, andjor compressor bleeds,generally illustrated by reference numeral 36.
The description above is for the purpose of describing in generalities a typical engine and since it doesn't form a part of this invention, except for the fact that existing components may be utilized ~o execute this invention a detailed description is omitted for the sake of convenience and simplicity. However for further details reference should be made to the literature of the engines noted above.
Referring to Fig. 1, this invention contemplates continual monitoring TIT or TET by suitable temperature sensors,such as thermocouple$or pyrometers and comparing its value with a referenced value in the comparator or : , ~
~7~L~L35 summing junction 40. If the value of the temperature is excessive (abnormally high) i.e. above ~he reference value, the output will be applied as one o the inputs to J'AND"
gate 42.
Likewise speed of the compressor, either Nl or N2 will be continuously monitored and when its rate of change as calculated by any suitable rate device or circuitry shown as box 44 exceeds a predetermined negative rate value it will be applied as the other input signal to "AND1' gate 42.
"~ND" gate 42 which is a well known element serves to provide an output solely when bo~h inputs are impressed thereon. When this occurs, a stall signal will be evidenced at the output.
This signal can be either utilized to activate a warning signal (sound or light) to the aircraft pilot or it may be utilized to indicate corrective action by changing engine inlet geometry 32 or engine exit geometry 38, angle of stator vane 34, compressor bleed 36 or shutoff or de-rich fuel.
Under certain circumstances it may be desirable to hold the stall signal for a predetermined time so that should the sensed parameters oscillate the stall detector may be repea~edly cycled on and off. In this event the control may include a suita~le latch and hold mechanism represented by box 45 which will hold the stall signal a predetermined time.
Timers of this type are well Icnown and commercially available.
~7 ~ ~3 ~
Referring to Fig. 2 where like numerals designate previously described elements the l'AND" gate 42 responds to the output oE comparator 40, which is an excessive TIT or TET and position of bleed 36. Likewise the outpu~ of ~'~ND"
gate 42 will produce a stall signal solely when both conditions exist.
By virtue of this invention stall detection is manifested by monitoring the TIT or TET and another engine operating parameter and computing it so that whenever an abnormal decrease in speed or an abnormal bleed opening occurs, a stall warning signal will be-lproduced, In certain engines the minimum fuel flow may be s~t too high under certain operating conditions and the stall signal may be utilized to re-set the minimum fuel flow to a lower value when the compressor is in stall. Otherwise, the amount of fuel permitting by the minimum fuel flow schedule before it was changed could cause the engine to overheat, even to an extent of burniRg it out.
It should be understood that the invention is not limited to the particular embodiments shown and described herein, but that various changes and modifications may be made without departing from the spirit or scope of this novel concept as defined by the following claims.
_g
~7~L~3~ ~
employed with this accelera~ion scheduling system, is to measure compressor discharge pressure and open compressor bleed valves whenever a predetermined compressor pressure change or rate of change occurs. And still another method ;~
which is described in U.S. Patent No. 3,867,717 and granted to John Theodore Moehring and Vigil Willis Lawson on February 18, 1975 is the utillzation of computed compressor pressures and turbine or exit temperatures as a means for determining when stall is present.
While such stall detection and prevention means as described above may be effective for cer~ain engines and/or their applications they are not always effective for other engines and/or their applications. For example, it may happen that under the same values of the comp~ted compressor pressures or their rates and turbine ~emperatures or their rates another engine operation may occur which would lead to a false indication o~ stall; or the monitoring of the parameter may not be readily accessible or the inclusion of the se~sing probes may interfere with the gas path and impair engine performance. ThereforP the selection of the stall controller comes down to what stall system is best for that engine and its applica~ions, what parameters are readily accessible, which system will provide the highest degree of accuracy, which one is fastest and a host of other considera-tions.
, ~7:L~35 This invention contemplates continuously monitoring two engine operating parameters and when both are at predetermined valuel the stall warning detector will produce an output signal.
Th~ output signal can then be utilized to provide a warning signal to the aircraft pilot, as by a visual or sound signal so that he can take corrective action, such as retarding the power lever. Additionally, this signal can be utilized to initiate corrective action in one of the following ways:
1. de-rich engine fuel flow 2. shutoff fuel open compressor bleeds 4. change compressor stator vane angle 5. change aircraft inlet geome~ry 6. change engine outlet geometry Furthermore the signal can be incorporated in a system that would initiate an automatic stall recovery sequen~e by shutting-ofE fuel, start ignition and reinitiate fuel flow in a timed sequence.
We have found that the turbine inlet temperature (TIT) or turbin~ exit temperature (TET) are viable parameters for indicating stall if these values are excessively high (or abnormally so) and that the speed of the compressor (either low compressor (Nl) or high compressor (N2) in a twin spool .
~C97~35 engine) is decreasing or not increasing. Also in engines that utilize compressor bleed valves and particularly the ones that are opened as a function of compressor pressure ratio, the temperature signal together with a bleed position signal can be utilized as an indication of stall or imminent stallO
In both situations, this invention contemplates continuously monitoring the turbine temperature and either compressor speed or compressor bleed valve position and apply computed values of these parameters to an l'AND1' gate to obtain an output signal indicative of stall solely when TIT or TET is excessively high and the bleeds are opened or when TIT or TET is excessively high and Nl or N2 is rapidly decreasing.
SUMMARY OF THE INVENTION
An object of this invention is to provide an improved stall warning system for an axial flow gas turbine engine.
A still further object of this invention is to provide a stall warning system that utilizes either TIT or TET
together with ano~her engine operating parameter solely when predetermined conditions of each signal is satisfied.
A still further object of this invention is to provide a stall warning system that produces an output signal solely when both TIT or TET are excessively high and the engine bleeds are opened~
~7~
A still further object of this invention is to provide a stall warning system that produces an output signal solely when TIT or TET is excessively high and Nl or N2 is at a predetenmined rate of decreasing speed.
In accordance with an embodiment of the invention, a stall detector system for an axial flow gas turbine engine has a compressor, a turbine and burner, bleed valve means for bleeding air from said compressor, means for detecting when stall is imminent including a temperature sensor measuring the temperature of the turbine, comparator means for producing a first signal whenever the measured temperature exceeds a referenced value, signal generator means responsive to the position of said bleed valve means for producing a second signal whenever the bleed valve means is open to bleed said compressor, and gate means responsive to both said first sig-nal and said second signal for producing a stall warning out-put signal whenever both the temperature of said turbine is abnormally high and said bleed valve means is bleeding air from said compressorO
From a differen~ aspect, and in accordance with the invention, the method of detecting stall in flow.g~s turbine engine that includes a compressor~ turbine and burner and compressor bleed vlaves comprises the steps of: measuring the temperature in proximity to the turbine so as to produce an output signal whenever this temperature is excessive in relation to normal engine operation, measuring the position of the compressor bleed valves so as to produce an output signal whenever the compressor bleed valves are opened, combining the outputs obtained in the steps of measuring so as to produce a signal indicative of stall solely when both output;signals are present which signal can then be used as a warning or to initiate corrective action.
~ - 6 -~L~7~35 Other features ~nd advantages will be apparent rom the specification and claims and from the accompanying draw-ings which illustrate an embodiment of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig. 1 is a schematic representation, partially in section of a gas turbine engine, and a schematic represen-tation of a stall warning system connected thereto.
Fig. 2 is a schematic representation of another embodiment of a stall warning system connected to a typical gas turbine engine.
DESCRIPTION OF THE PREFERRED EMBODIMENT
For the purpose of this description, the gas turbine engine illustrated in Fig. 1 typifies any number of different types of engines where this invention may be utilized. Such engines may include, as for example, the JT-3D, JT-8D, JT- ;
9D, TF-30, ~T-12 manufactured by the Pratt & W~litney Aircraft Division of United Technologies Corporation, but are not limited thereto. Suffice it to say that this invention is applicable where stall is a problem which is generally the case in any axial flow compressor.
- 6a -.~
`~D , ,. . :
~ 3 ~
Es6entially, the gas turbine engine exemplified by Fig, 1 is a twin spool a~ial flow gas turbine engine having an engine casing 10 in which the low pressure compressor 12 and driving turbine 14 and high pressure compressor 16 and its driving turbine 18 are rotary mounted. The burner section 20 which burns fuel metered thereto by fuel control (not shown) generates gases for driving the turbines which then are exhausted through a nozzle to produce thrust or the thrust is augmented by a suitable af~erburner 24. :~
Depending on the particular engine and its application it may include a variable geometry inlet duct 32, variable compressor stators generally illustrated by referen~e numeral 34, andjor compressor bleeds,generally illustrated by reference numeral 36.
The description above is for the purpose of describing in generalities a typical engine and since it doesn't form a part of this invention, except for the fact that existing components may be utilized ~o execute this invention a detailed description is omitted for the sake of convenience and simplicity. However for further details reference should be made to the literature of the engines noted above.
Referring to Fig. 1, this invention contemplates continual monitoring TIT or TET by suitable temperature sensors,such as thermocouple$or pyrometers and comparing its value with a referenced value in the comparator or : , ~
~7~L~L35 summing junction 40. If the value of the temperature is excessive (abnormally high) i.e. above ~he reference value, the output will be applied as one o the inputs to J'AND"
gate 42.
Likewise speed of the compressor, either Nl or N2 will be continuously monitored and when its rate of change as calculated by any suitable rate device or circuitry shown as box 44 exceeds a predetermined negative rate value it will be applied as the other input signal to "AND1' gate 42.
"~ND" gate 42 which is a well known element serves to provide an output solely when bo~h inputs are impressed thereon. When this occurs, a stall signal will be evidenced at the output.
This signal can be either utilized to activate a warning signal (sound or light) to the aircraft pilot or it may be utilized to indicate corrective action by changing engine inlet geometry 32 or engine exit geometry 38, angle of stator vane 34, compressor bleed 36 or shutoff or de-rich fuel.
Under certain circumstances it may be desirable to hold the stall signal for a predetermined time so that should the sensed parameters oscillate the stall detector may be repea~edly cycled on and off. In this event the control may include a suita~le latch and hold mechanism represented by box 45 which will hold the stall signal a predetermined time.
Timers of this type are well Icnown and commercially available.
~7 ~ ~3 ~
Referring to Fig. 2 where like numerals designate previously described elements the l'AND" gate 42 responds to the output oE comparator 40, which is an excessive TIT or TET and position of bleed 36. Likewise the outpu~ of ~'~ND"
gate 42 will produce a stall signal solely when both conditions exist.
By virtue of this invention stall detection is manifested by monitoring the TIT or TET and another engine operating parameter and computing it so that whenever an abnormal decrease in speed or an abnormal bleed opening occurs, a stall warning signal will be-lproduced, In certain engines the minimum fuel flow may be s~t too high under certain operating conditions and the stall signal may be utilized to re-set the minimum fuel flow to a lower value when the compressor is in stall. Otherwise, the amount of fuel permitting by the minimum fuel flow schedule before it was changed could cause the engine to overheat, even to an extent of burniRg it out.
It should be understood that the invention is not limited to the particular embodiments shown and described herein, but that various changes and modifications may be made without departing from the spirit or scope of this novel concept as defined by the following claims.
_g
Claims (5)
1. A stall detector system for an axial flow gas turbine engine having a compressor, turbine and burner, bleed valve means for bleeding air from said compressor, means for detecting when stall is imminent including a temperature sensor measuring the temperature of the turbine, comparator means for producing a first signal whenever the measured temperature exceeds a referenced value, signal generator means responsive to the position of said bleed valve means for prod-ucing a second signal whenever the bleed valve means is open to bleed said compressor, and gate means responsive to both said first signal and said second signal for producing a stall warning output signal whenever both the temperature of said turbine is abnormally high and said bleed valve means is bleeding air from said compressor.
2. A stall indicator as claimed in claim 1 wherein said temperature sensor senses the turbine inlet temperature.
3. A stall indicator as claimed in claim 1 wherein said temperature sensor senses the turbine exit temperature.
4 The method of detecting stall in flow gas turbine engine that includes a compressor, turbine and burner and compressor bleed valves comprising the steps of:
measuring the temperature in proximity to the turbine so as to produce an output signal whenever this tem-perature is excessive in relation to normal engine operation, measuring the position of the compressor bleed valves so as to produce an output signal whenever the compressor bleed valves are opened, combining the outputs obtained in the steps of measuring so as to produce a signal indicative of stall solely when both output signals are present which signal can then be used as a warning or to initiate corrective action.
measuring the temperature in proximity to the turbine so as to produce an output signal whenever this tem-perature is excessive in relation to normal engine operation, measuring the position of the compressor bleed valves so as to produce an output signal whenever the compressor bleed valves are opened, combining the outputs obtained in the steps of measuring so as to produce a signal indicative of stall solely when both output signals are present which signal can then be used as a warning or to initiate corrective action.
5. The method as claimed in claim 4 including the step of holding the output signal obtained in the step of combining for a predetermined time interval so as not to release this output signal prematurely.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US05/633,308 US4060979A (en) | 1975-11-19 | 1975-11-19 | Stall warning detector for gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1071435A true CA1071435A (en) | 1980-02-12 |
Family
ID=24539119
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA264,759A Expired CA1071435A (en) | 1975-11-19 | 1976-11-01 | Stall warning detector for gas turbine engine |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US4060979A (en) |
| BE (1) | BE848419A (en) |
| CA (1) | CA1071435A (en) |
| DE (1) | DE2652730A1 (en) |
| FR (1) | FR2332427A1 (en) |
| GB (1) | GB1505790A (en) |
| NL (1) | NL7612419A (en) |
| SE (1) | SE7612418L (en) |
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| FR2488696A1 (en) * | 1980-08-13 | 1982-02-19 | Snecma | METHOD AND APPARATUS FOR DETECTING ROTATING FLASHING APPEARING IN A TURBOMACHINE WITH TWO ROTATING BODIES |
| GB2126382B (en) * | 1982-08-10 | 1986-01-08 | Nissan Motor | Gas turbine engine control system |
| DE3582821D1 (en) * | 1984-05-14 | 1991-06-20 | Dresser Ind | SYSTEM, DEVICE AND METHOD FOR DETECTING AND CONTROLLING THE PUMP IN A TURBO COMPRESSOR. |
| US4836016A (en) * | 1985-08-10 | 1989-06-06 | Toyota Jidosha Kabushiki Kaisha | Method and apparatus for detecting abnormal state in pulse train generating sensor |
| US4756152A (en) * | 1986-12-08 | 1988-07-12 | United Technologies Corporation | Control for bleed modulation during engine deceleration |
| US4894782A (en) * | 1987-12-18 | 1990-01-16 | United Technologies Corporation | Diagnostic system for determining engine start bleed strap failure |
| USRE34388E (en) * | 1989-04-13 | 1993-09-28 | General Electric Company | Method and apparatus for detecting stalls |
| US5012637A (en) * | 1989-04-13 | 1991-05-07 | General Electric Company | Method and apparatus for detecting stalls |
| US5051918A (en) * | 1989-09-15 | 1991-09-24 | United Technologies Corporation | Gas turbine stall/surge identification and recovery |
| US5375412A (en) * | 1993-04-26 | 1994-12-27 | United Technologies Corporation | Rotating stall recovery |
| US5726891A (en) * | 1994-01-26 | 1998-03-10 | Sisson; Patterson B. | Surge detection system using engine signature |
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| AU2002220089A1 (en) * | 2000-11-14 | 2002-05-27 | Capstone Turbine Corporation | Method and apparatus for turbogenerator anti-surge control |
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| US7762084B2 (en) * | 2004-11-12 | 2010-07-27 | Rolls-Royce Canada, Ltd. | System and method for controlling the working line position in a gas turbine engine compressor |
| GB0518659D0 (en) * | 2005-09-13 | 2005-10-19 | Rolls Royce Plc | Health monitoring |
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| US7679529B2 (en) * | 2006-12-07 | 2010-03-16 | The Boeing Company | Method and apparatus for indicating operational state of aircraft engine |
| US8074498B2 (en) * | 2009-05-18 | 2011-12-13 | United Technologies Corporation | System and method of assessing thermal energy levels of a gas turbine engine component |
| US8204671B2 (en) * | 2009-05-18 | 2012-06-19 | United Technologies Corporation | System and method of estimating gas turbine engine performance |
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| FR2962500B1 (en) * | 2010-07-08 | 2012-09-14 | Snecma | METHOD AND DEVICE FOR DETECTING ROTATING DECOLUTION AFFECTING A TURBOMACHINE COMPRESSOR |
| US9068463B2 (en) * | 2011-11-23 | 2015-06-30 | General Electric Company | System and method of monitoring turbine engines |
| JP6738601B2 (en) | 2015-11-04 | 2020-08-12 | 三菱日立パワーシステムズ株式会社 | Gas turbine starting method and apparatus |
| FR3063782B1 (en) * | 2017-03-07 | 2021-06-18 | Safran Aircraft Engines | METHOD AND DEVICE FOR DETECTION OF CONDITIONS FRIENDLY TO THE APPEARANCE OF PUMPING WITH A VIEW TO PROTECTING A COMPRESSOR OF AN AIRCRAFT TURBOMACHINE |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3137210A (en) * | 1960-07-21 | 1964-06-16 | United Aircraft Corp | Pressure ratio bleed control |
| US3172259A (en) * | 1962-03-02 | 1965-03-09 | Avco Corp | Variable geometry control for gas turbine engines |
| US3426322A (en) * | 1965-10-28 | 1969-02-04 | Gen Electric | Turbojet compressor stall warning indicator |
| US3395534A (en) * | 1966-06-29 | 1968-08-06 | Gen Electric | Speed responsive and control systems for rotors |
| US3688504A (en) * | 1970-11-27 | 1972-09-05 | Gen Electric | Bypass valve control |
| US3759037A (en) * | 1972-01-27 | 1973-09-18 | Westinghouse Electric Corp | Over temperature protection system for a gas turbine |
| GB1415681A (en) * | 1972-06-24 | 1975-11-26 | Rolls Royce | Flame-out control in gas turbine engine |
| US3867717A (en) * | 1973-04-25 | 1975-02-18 | Gen Electric | Stall warning system for a gas turbine engine |
| US3876326A (en) * | 1974-01-30 | 1975-04-08 | Simmonds Precision Products | Surge control system |
-
1975
- 1975-11-19 US US05/633,308 patent/US4060979A/en not_active Expired - Lifetime
-
1976
- 1976-11-01 CA CA264,759A patent/CA1071435A/en not_active Expired
- 1976-11-08 SE SE7612418A patent/SE7612418L/en not_active Application Discontinuation
- 1976-11-09 NL NL7612419A patent/NL7612419A/en not_active Application Discontinuation
- 1976-11-16 GB GB47668/76A patent/GB1505790A/en not_active Expired
- 1976-11-17 FR FR7634562A patent/FR2332427A1/en active Pending
- 1976-11-17 BE BE172426A patent/BE848419A/en unknown
- 1976-11-19 DE DE19762652730 patent/DE2652730A1/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| BE848419A (en) | 1977-03-16 |
| FR2332427A1 (en) | 1977-06-17 |
| NL7612419A (en) | 1977-05-23 |
| SE7612418L (en) | 1977-05-20 |
| DE2652730A1 (en) | 1977-05-26 |
| US4060979A (en) | 1977-12-06 |
| GB1505790A (en) | 1978-03-30 |
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