CA1274606A - Gas turbine engine control - Google Patents
Gas turbine engine controlInfo
- Publication number
- CA1274606A CA1274606A CA000493270A CA493270A CA1274606A CA 1274606 A CA1274606 A CA 1274606A CA 000493270 A CA000493270 A CA 000493270A CA 493270 A CA493270 A CA 493270A CA 1274606 A CA1274606 A CA 1274606A
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- CA
- Canada
- Prior art keywords
- error
- engine
- temperature
- gas turbine
- turbine engine
- 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 - Fee Related
Links
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
GAS TURBINE ENGINE CONTROL
ABSTRACT OF THE DISCLOSURE
In one form of the present invention, the thrust of a gas turbine engine is inferred. If a droop in thrust is predicted, components of the engine are modulated in response to restore thrust.
ABSTRACT OF THE DISCLOSURE
In one form of the present invention, the thrust of a gas turbine engine is inferred. If a droop in thrust is predicted, components of the engine are modulated in response to restore thrust.
Description
GAS TURBINE ~NGI~E CONTRO~
The present invention relates to gas turbine engine controls and, more specifically, to a type of control termed a thrust droop compensator. Such a compensator reduces the droop in thrust which sometimes occurs because o~ di~ferent rates of thermal growth of different engine components during engine acceleration.
BACKGROUND OF THE INYENTION
Pigure 1 illustrates a gas turbine aircraft engine as known in the art. Ho~ gases 3 provided by a combustor 6 impart energy to a high pressure turbine 9 which is surrounded by a shroud 12. A tip clearance 15 exists between the turbine 9 and the shroud 12. When the engine is idling, say at 11770 rpm, a given tip clearance will exist, such as 0.047 inches. However, during a sudden acceleration, such as to 16140 rpm within 4 seconds, increases in centrifugal forces due to the greater rotational speed causes the turbine to expand) thus reducing the tip clearance to .016 inches. Temperature in the region of the high pressure turbine 9 will increase, thus causing the turbine 9 and the shroud 12 to expand thermally. However, since the thermal mass of the shroud 12 is much less than that o~
the turbine 9, the shroud 12 heats up faster, and thus expands faster. Accordingly, the tip clearance 15 initially increases, say to .028 inches, and then decreases to the steady-state level of 0.016 inches when the temperature o~ the turbine 9 reaches its steady-state value.
This initial increased tip clearance 15 is undesirable because it imposes a penalty in engine 13L~ 2 efficiency: the hot gases 3 can bypass the turbine 5 by leakin~ through the tip clearance region 15, and thus the leaking gases do little or no work upon the turbine 9.
OBJECTS OF THE INVENTION
It is an object of the present inYention to provide a new and improved gas turbine engine control.
It is a further object of the present invention to provide a new and improved gas turbine engine control which compensates for thrust droop occurring after engine acceleration.
SUMMARY OF THE INV~NTION
In one form of the present invention, the ~hrust of a gas turbine engine is inferred. If a droop in thrust is predicted, components of the engine are modulated in response to restore thrust.
BRIEF DESCRIPTION OF THE DRAWING
FIGVRE 1 illustrates a gas turbine engine.
FIGURES 2-5 illustrate the changes experienced by various engine components with time during acceleration.
FIGU~E 6 illustrates one form of the present invention.
DETAILED DESCRIPTION OF THE INVENTION
Figure 2 illustrates a plot of the transient 16 of the temperature (termed T5) of the exhaust of a low pressure turbine 18 during acceleration. T5 is measured at point 21 at Figure 1, downs~ream of the low pressure turbine 18. The vertical axis in Figure 2 displays T5 in degrees F, but referenced to an arbitrary zero which is actually the maximum scheduled temperature for T5 which, in practice, is about 1500 F. During the 60 second interval 24 and earlier, the engine is operating at idle, and at time T = 0, the engine is accelerated, causing T5 to rapidly increase by about 800~ F within the 4-second interval 27.
Figures 3-5 illustrate the effect of this rapid increase in T5 upon the temperatures of the turbine 9 and the shroud 12 of Figure 1. Figure 3 illustrates the transient 30 of the shroud diameter, and Figure 4 illustrates the transient 33 of the turbine diameter, both as functions of time. The vertical axes in both these Figures are plotted in arbitrary units of diameter Measure. However, even though both the turbine 9 and the shroud 12 expand upon being heated, the shroud transient is given a positive slope while the turbine transient 33 is given a negative slope. This is because the plots are referenced to the tip clearance 15 in Figure 1, and not to absolute diameter. Since e~pansion o~ the shroud 12 in Figure 1 causes tip clearance 15 to increase, the shroud transient 30 in Figure 3 is ascribed a positive slope. However, since the expansion of the turbine 9 causes tip clearance 15 to decrease, the turbine transient 33 is ascribed a negative slope.
The transients of Figures 3 and 4 are algebraically added to produce transient 36 in Figure 5. Transient 36 illustrates the net tip clearance 15 in Figure 1 as a function of time during the acceleration. Again, the vertical axis in Figure 5 is in arbitrary units indicative of clearance size. The reader will note that there is initially a peak clearance at point 39 which gradually decreases toward the steady-state value 42. As the Figure shows, it takes approximately 4 or 5 minutes for the tip clearance 15 to reach its steady-state value 42.
Figure 6 illustrates one form of the present invention which compensates for the effect of the tip clearance transient 36 in Figure 5 upon thrust. Block 50 in Figure 6 generates a digital output versus time signal which is similar to the transient 30 of Figure ~ZZ~; 1 3 LN -1~ g 2 3, and block 53 generates a signal similar to the transient 33 of Figure 4. The summation in summer 56 in Figure 6 produces a net output on line 59 similar to the transient 36 of Figure 5. The net output is subtracted from summer 62 in Figure 6 in which the actual, measured, T5 is added by block 64 on line 65.
Also subtracted in summer 62 is a T5 reference derived from a schedule indicated by block 68. The latter block 68 is a schedule, or listing, of various Yalues of T5 which are calculated in advance for various engine operating conditions. Thus, the value subtracted at summer 62 by block 68 will change, depending upon the operating condition of the engine.
Blocks 64 and 68 (ignoring the effect of the net ou~put on line 59) pro~ide on line 72 a T5 ERROR
signal, in the sense that the error signal indicates a deviation of actual T5 from scheduled T5. The addition of the net output (from summer 56) on line 59 modifies the T5 ERROR signal into a T5 FRROR signal, but droop compensated (T5E-DC). TSE-DC is integrated in block 75 designated by the symbol l/S (l/S being a/LaPlace transform term) and having a gain indicated by the term K. The output, on line 78, is a Yariable exhaust nozzle (VEN) area trim signal.
The VEN refers to a nozzle 95 in ~igure 1 which is modulated in area as shown by dashed nozzle 95A to modify the pressure at poin~ 21 in the engine.
This pTeSSUre modification, in a manner which need not be understood here, alters the thrust produced by the engine. Control of the modulation is accomplished by apparatus which is known in the art and outlined below. The signal provided by block 101, a VEN area demand signal on line 103, is added in summer 105.
Subtracted from summer 105 is the output of summer 108 which receives as inputs a feedback signal along line 110 which is provided by a transducer (not shown) which measures the actual V~N area. The other input o summer 10~ is the VFN trim signal on line 73 and it is subtracted therein~ The output of summer 105, on line 115, is processed as known in the art by VEN orward path dynamics block 120, which includes digital filters to stabilize the VEN control loop and the necessary analog electric and hydromechanical components to modulate nozzle area 95 in Figures 1 and 6.
The operation of the circuitry shown in Figure 6 can be described as follows. During the T5 transient 16 of Figure 2, a signal resembling the net output plot 36 of Figure 5 is subtracted, in Figure 6, from summer 62 by means of line 59. This, in effect, raises the T5 reference of block 68, because both the signals from summer 56 and block 68 are applied to summer 62 with the same algebraic sign. Therefore, the T5 ERROR
signal on line 72 becomes larger, so that the VEN trim signal on line 78 induces the VEN area to approach a size which will reduce the T5 ERROR, and thus increase thrust. (It has been found empirically that thrust is a function of T5, and, further, a generally linear function at intermediate thrusts, so that control of T5 is tantamount to control of thrust.) Symbols 110, 112, and 114 indicate signal limiters, known in the art, which are considered self-explanatory. For example, limiter 110 limits the signal allowed to appear on line 116 to a range representing 0 and -123 F. _ _ The term in block 50, namely, 1rl , is a LaPlace transform. Thus, the signal p rocess ng which occurs between point 120 and point 122 can be described by the following transfer function (ignoring the action of the limiters such as limiter 110):
T5 COMP = [T5-T5RE~ ~ ~ + ~5-T5RE3 ~ ~
wherein TSCOMP is the signal generated on line 59.
13LN-16g2 An invention has been described wherein a droop in thrust occurring during acceleration o a gas turbine engine is compensated. The droop is caused by the transient increase in tip clearance between the high pressure turbine and the shroud surrounding it.
The clearance transient is caused by ~he differential thermal growth of the turbine as opposed to the shroud. The present invention increases engine thrust, as by manipulating parameters such as exhaust nozzle area and fuel flow, as a function of tip clearance in order to compensate for the loss induced by the clearance transient.
One important aspect of the invention is that the general shapes of the signals produced by blocks 50 and 53 in Figure 6 are predeteremined. That is, the signals decay with predetermined time constants as do the signals shown in Figures 3 and 4. However, the initial magnitudes of the signals produced by these blocks is a function of the signal present on line 122 in Figure 6. In this sense, the signals produced by blocks 50 and 53 are produced according to predetermined functions: the decay times (dictated by the time constants in blocks 50 and 53) are predetermined, but the initial magnitudes are dictated by T5 ERROR.
Numerous modifications and subs~itutions can be undertaken without departing from the true spirit and scope of the present invention. For example, one embodiment has been tested in which the following variables were given the following values:
rl = 10 *18583~0.5 ~FMCJ
r2 = 85 *~8583l0.5 \WFMCJ
13L~ 162 wherein the term WFMC refers to the fuel flow (in pounds per hour), but corrected for the sea level static fuel re~uirement at intermediate power. MaXing the time constants ~1 and ~2 variable in this manner corrects for the effect of Reynolds number on heat transfer to the turbine disk 9 in Figure 1 and shroud 12 in Figure 1.
However, it is to be recognized that it will be known to those skilled in the art that controls for different engines using the concept of the present invention will almost certainly require different values for these variables. The Yalues for a different engine can be calculated from the Figure 5 type of transient which corresponds to that engine. The time constants,~ and ~ , are calculated from the time constants of the plots of Figures 3 and 4, and the gains ~, are calculated, as known in the art, to give proper magnitude to the signal appearing on line 59 in Figure 6.
The present invention relates to gas turbine engine controls and, more specifically, to a type of control termed a thrust droop compensator. Such a compensator reduces the droop in thrust which sometimes occurs because o~ di~ferent rates of thermal growth of different engine components during engine acceleration.
BACKGROUND OF THE INYENTION
Pigure 1 illustrates a gas turbine aircraft engine as known in the art. Ho~ gases 3 provided by a combustor 6 impart energy to a high pressure turbine 9 which is surrounded by a shroud 12. A tip clearance 15 exists between the turbine 9 and the shroud 12. When the engine is idling, say at 11770 rpm, a given tip clearance will exist, such as 0.047 inches. However, during a sudden acceleration, such as to 16140 rpm within 4 seconds, increases in centrifugal forces due to the greater rotational speed causes the turbine to expand) thus reducing the tip clearance to .016 inches. Temperature in the region of the high pressure turbine 9 will increase, thus causing the turbine 9 and the shroud 12 to expand thermally. However, since the thermal mass of the shroud 12 is much less than that o~
the turbine 9, the shroud 12 heats up faster, and thus expands faster. Accordingly, the tip clearance 15 initially increases, say to .028 inches, and then decreases to the steady-state level of 0.016 inches when the temperature o~ the turbine 9 reaches its steady-state value.
This initial increased tip clearance 15 is undesirable because it imposes a penalty in engine 13L~ 2 efficiency: the hot gases 3 can bypass the turbine 5 by leakin~ through the tip clearance region 15, and thus the leaking gases do little or no work upon the turbine 9.
OBJECTS OF THE INVENTION
It is an object of the present inYention to provide a new and improved gas turbine engine control.
It is a further object of the present invention to provide a new and improved gas turbine engine control which compensates for thrust droop occurring after engine acceleration.
SUMMARY OF THE INV~NTION
In one form of the present invention, the ~hrust of a gas turbine engine is inferred. If a droop in thrust is predicted, components of the engine are modulated in response to restore thrust.
BRIEF DESCRIPTION OF THE DRAWING
FIGVRE 1 illustrates a gas turbine engine.
FIGURES 2-5 illustrate the changes experienced by various engine components with time during acceleration.
FIGU~E 6 illustrates one form of the present invention.
DETAILED DESCRIPTION OF THE INVENTION
Figure 2 illustrates a plot of the transient 16 of the temperature (termed T5) of the exhaust of a low pressure turbine 18 during acceleration. T5 is measured at point 21 at Figure 1, downs~ream of the low pressure turbine 18. The vertical axis in Figure 2 displays T5 in degrees F, but referenced to an arbitrary zero which is actually the maximum scheduled temperature for T5 which, in practice, is about 1500 F. During the 60 second interval 24 and earlier, the engine is operating at idle, and at time T = 0, the engine is accelerated, causing T5 to rapidly increase by about 800~ F within the 4-second interval 27.
Figures 3-5 illustrate the effect of this rapid increase in T5 upon the temperatures of the turbine 9 and the shroud 12 of Figure 1. Figure 3 illustrates the transient 30 of the shroud diameter, and Figure 4 illustrates the transient 33 of the turbine diameter, both as functions of time. The vertical axes in both these Figures are plotted in arbitrary units of diameter Measure. However, even though both the turbine 9 and the shroud 12 expand upon being heated, the shroud transient is given a positive slope while the turbine transient 33 is given a negative slope. This is because the plots are referenced to the tip clearance 15 in Figure 1, and not to absolute diameter. Since e~pansion o~ the shroud 12 in Figure 1 causes tip clearance 15 to increase, the shroud transient 30 in Figure 3 is ascribed a positive slope. However, since the expansion of the turbine 9 causes tip clearance 15 to decrease, the turbine transient 33 is ascribed a negative slope.
The transients of Figures 3 and 4 are algebraically added to produce transient 36 in Figure 5. Transient 36 illustrates the net tip clearance 15 in Figure 1 as a function of time during the acceleration. Again, the vertical axis in Figure 5 is in arbitrary units indicative of clearance size. The reader will note that there is initially a peak clearance at point 39 which gradually decreases toward the steady-state value 42. As the Figure shows, it takes approximately 4 or 5 minutes for the tip clearance 15 to reach its steady-state value 42.
Figure 6 illustrates one form of the present invention which compensates for the effect of the tip clearance transient 36 in Figure 5 upon thrust. Block 50 in Figure 6 generates a digital output versus time signal which is similar to the transient 30 of Figure ~ZZ~; 1 3 LN -1~ g 2 3, and block 53 generates a signal similar to the transient 33 of Figure 4. The summation in summer 56 in Figure 6 produces a net output on line 59 similar to the transient 36 of Figure 5. The net output is subtracted from summer 62 in Figure 6 in which the actual, measured, T5 is added by block 64 on line 65.
Also subtracted in summer 62 is a T5 reference derived from a schedule indicated by block 68. The latter block 68 is a schedule, or listing, of various Yalues of T5 which are calculated in advance for various engine operating conditions. Thus, the value subtracted at summer 62 by block 68 will change, depending upon the operating condition of the engine.
Blocks 64 and 68 (ignoring the effect of the net ou~put on line 59) pro~ide on line 72 a T5 ERROR
signal, in the sense that the error signal indicates a deviation of actual T5 from scheduled T5. The addition of the net output (from summer 56) on line 59 modifies the T5 ERROR signal into a T5 FRROR signal, but droop compensated (T5E-DC). TSE-DC is integrated in block 75 designated by the symbol l/S (l/S being a/LaPlace transform term) and having a gain indicated by the term K. The output, on line 78, is a Yariable exhaust nozzle (VEN) area trim signal.
The VEN refers to a nozzle 95 in ~igure 1 which is modulated in area as shown by dashed nozzle 95A to modify the pressure at poin~ 21 in the engine.
This pTeSSUre modification, in a manner which need not be understood here, alters the thrust produced by the engine. Control of the modulation is accomplished by apparatus which is known in the art and outlined below. The signal provided by block 101, a VEN area demand signal on line 103, is added in summer 105.
Subtracted from summer 105 is the output of summer 108 which receives as inputs a feedback signal along line 110 which is provided by a transducer (not shown) which measures the actual V~N area. The other input o summer 10~ is the VFN trim signal on line 73 and it is subtracted therein~ The output of summer 105, on line 115, is processed as known in the art by VEN orward path dynamics block 120, which includes digital filters to stabilize the VEN control loop and the necessary analog electric and hydromechanical components to modulate nozzle area 95 in Figures 1 and 6.
The operation of the circuitry shown in Figure 6 can be described as follows. During the T5 transient 16 of Figure 2, a signal resembling the net output plot 36 of Figure 5 is subtracted, in Figure 6, from summer 62 by means of line 59. This, in effect, raises the T5 reference of block 68, because both the signals from summer 56 and block 68 are applied to summer 62 with the same algebraic sign. Therefore, the T5 ERROR
signal on line 72 becomes larger, so that the VEN trim signal on line 78 induces the VEN area to approach a size which will reduce the T5 ERROR, and thus increase thrust. (It has been found empirically that thrust is a function of T5, and, further, a generally linear function at intermediate thrusts, so that control of T5 is tantamount to control of thrust.) Symbols 110, 112, and 114 indicate signal limiters, known in the art, which are considered self-explanatory. For example, limiter 110 limits the signal allowed to appear on line 116 to a range representing 0 and -123 F. _ _ The term in block 50, namely, 1rl , is a LaPlace transform. Thus, the signal p rocess ng which occurs between point 120 and point 122 can be described by the following transfer function (ignoring the action of the limiters such as limiter 110):
T5 COMP = [T5-T5RE~ ~ ~ + ~5-T5RE3 ~ ~
wherein TSCOMP is the signal generated on line 59.
13LN-16g2 An invention has been described wherein a droop in thrust occurring during acceleration o a gas turbine engine is compensated. The droop is caused by the transient increase in tip clearance between the high pressure turbine and the shroud surrounding it.
The clearance transient is caused by ~he differential thermal growth of the turbine as opposed to the shroud. The present invention increases engine thrust, as by manipulating parameters such as exhaust nozzle area and fuel flow, as a function of tip clearance in order to compensate for the loss induced by the clearance transient.
One important aspect of the invention is that the general shapes of the signals produced by blocks 50 and 53 in Figure 6 are predeteremined. That is, the signals decay with predetermined time constants as do the signals shown in Figures 3 and 4. However, the initial magnitudes of the signals produced by these blocks is a function of the signal present on line 122 in Figure 6. In this sense, the signals produced by blocks 50 and 53 are produced according to predetermined functions: the decay times (dictated by the time constants in blocks 50 and 53) are predetermined, but the initial magnitudes are dictated by T5 ERROR.
Numerous modifications and subs~itutions can be undertaken without departing from the true spirit and scope of the present invention. For example, one embodiment has been tested in which the following variables were given the following values:
rl = 10 *18583~0.5 ~FMCJ
r2 = 85 *~8583l0.5 \WFMCJ
13L~ 162 wherein the term WFMC refers to the fuel flow (in pounds per hour), but corrected for the sea level static fuel re~uirement at intermediate power. MaXing the time constants ~1 and ~2 variable in this manner corrects for the effect of Reynolds number on heat transfer to the turbine disk 9 in Figure 1 and shroud 12 in Figure 1.
However, it is to be recognized that it will be known to those skilled in the art that controls for different engines using the concept of the present invention will almost certainly require different values for these variables. The Yalues for a different engine can be calculated from the Figure 5 type of transient which corresponds to that engine. The time constants,~ and ~ , are calculated from the time constants of the plots of Figures 3 and 4, and the gains ~, are calculated, as known in the art, to give proper magnitude to the signal appearing on line 59 in Figure 6.
Claims (4)
1. A gas turbine engine control comprising:
(a) temperature error means for deriving an error signal, T5 ERROR, indicative of the deviation of the temperature of an engine component from a reference temperature;
(b) variable exhaust nozzle (VEN) means for modifying the area of the exhaust nozzle of the engine as a function of T5 ERROR; and (c) T5 ERROR compensation means for modifying T5 ERROR such that T5 ERROR first increases then decreases to thereby induce the VEN means to first decrease and then increase the nozzle area.
(a) temperature error means for deriving an error signal, T5 ERROR, indicative of the deviation of the temperature of an engine component from a reference temperature;
(b) variable exhaust nozzle (VEN) means for modifying the area of the exhaust nozzle of the engine as a function of T5 ERROR; and (c) T5 ERROR compensation means for modifying T5 ERROR such that T5 ERROR first increases then decreases to thereby induce the VEN means to first decrease and then increase the nozzle area.
2. In a gas turbine engine control which modulates a variable exhaust nozzle as a function of parameters which include a temperature error signal, T5 ERROR, derived from comparison of the temperature of a component of the engine with a reference schedule of temperatures, the improvement comprising:
(a) first modification means for modifying T5 ERROR;
(b) second modification means for modifying T5 ERROR such that the combined effect of the first and second modification means is to initially increase T5 ERROR according to a predetermined time constant and then to decrease T5 ERROR according to a predetermined second time constant.
(a) first modification means for modifying T5 ERROR;
(b) second modification means for modifying T5 ERROR such that the combined effect of the first and second modification means is to initially increase T5 ERROR according to a predetermined time constant and then to decrease T5 ERROR according to a predetermined second time constant.
3. In a control according to claim 2 in which (a) the first modification means modifies T5 ERROR substantially according to the following LaPlace transform:
(b) the second modification means modifies T5 ERROR substantially according to the following LaPlace transform:
in which T2 > T1.
(b) the second modification means modifies T5 ERROR substantially according to the following LaPlace transform:
in which T2 > T1.
4. A method of compensating for the droop in thrust which occurs in a gas turbine engine upon acceleration, comprising the following steps:
(a) inferring the occurrence of droop from a change in the temperature of the low pressure turbine exhaust T5;
(b) increasing and then decreasing the difference between T5 and a reference to produce a compen-sated temperature signal, T5 COMP; and (c) modulating the exhaust nozzle area of the engine as a function of T5 COMP.
(a) inferring the occurrence of droop from a change in the temperature of the low pressure turbine exhaust T5;
(b) increasing and then decreasing the difference between T5 and a reference to produce a compen-sated temperature signal, T5 COMP; and (c) modulating the exhaust nozzle area of the engine as a function of T5 COMP.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000493270A CA1274606A (en) | 1985-10-18 | 1985-10-18 | Gas turbine engine control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA000493270A CA1274606A (en) | 1985-10-18 | 1985-10-18 | Gas turbine engine control |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1274606A true CA1274606A (en) | 1990-09-25 |
Family
ID=4131658
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000493270A Expired - Fee Related CA1274606A (en) | 1985-10-18 | 1985-10-18 | Gas turbine engine control |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA1274606A (en) |
-
1985
- 1985-10-18 CA CA000493270A patent/CA1274606A/en not_active Expired - Fee Related
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| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |