JP2004308597A - High altitude performance testing device and pressure control method for the same - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a reliable high altitude performance testing device and a pressure control method for the same capable of precisely keeping internal pressure at a predetermined test pressure in corresponding to the variation of the exhaust gas quantity in an engine performance test and capable of continuously testing stably for a long period of time without possibility of surge and choke. <P>SOLUTION: Gas in a sealed chamber 10 housing an aircraft engine 1 is sucked, compressed to atmospheric pressure and discharged to an outside by an axial compressor 12. Fresh air quantity supplied to the inlet side of the axial compressor 12 is simultaneously controlled to maintain a pressure ratio of the axial compressor constant. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

[0001]
[Industrial applications]
The present invention relates to a high altitude performance test apparatus and a pressure control method thereof.
[0002]
[Prior art]
High altitude performance test devices have been proposed to test engine performance by simulating a high altitude flight state of an aircraft engine (for example, Patent Documents 1 and 2).
[0003]
As shown in FIG. 5, the "aviation engine test device" of [Patent Document 1] has a branch point 62 between a test chamber 51 and a temperature control device 55, and a connection between the test chamber 51 and an exhaust cooling device 59. A junction 63 is provided between them, and the junction 62 and the junction 63 are connected by a bypass line 64. An adjustment valve 65 for adjusting the flow rate is provided in the bypass line 64, and the opening degree of the adjustment valve 65 can be maintained at a constant pressure in the air supply chamber 52 and the exhaust chamber 53 in accordance with a change in the output of the test engine 54. Is controlled by the control device 66 as described above.
[0004]
As shown in FIG. 6, a “high altitude environment simulation test facility” of [Patent Document 2] includes a high altitude environment test chamber 71, a blower 74 that takes in air 73 from the atmosphere and sends it to the test chamber 71 under pressure, and a blower 74. A high altitude provided with an expander 76 for reducing the pressure and lowering the temperature by expanding the air 73 from the air to the test chamber 71 and a blower 77 for forcibly sucking the air 73 from the test chamber 71 and discharging the air 73 to the atmosphere. In the environment simulation test facility, an ejector 78 is provided on the upstream side of the exhaust fan 77 instead of installing the same exhaust fan 77 in multiple stages, and the air 73 pressure-fed from the blower 74 is diverted to supply the working air to the ejector 78. A bypass passage 79 is provided to guide the flow.
[0005]
Further, as pressure control means of a compressor, Patent Literature 3, Patent Literature 4, and the like are known.
[0006]
[Patent Document 3] "Inlet guide vane device for aero engine and control method thereof", as shown in FIG. 7, a plurality of inlet guide vanes installed in front of a rotor row constituting a compressor of an aero engine. 82, a plurality of actuators 84 provided for each inlet guide vane and individually correcting the installation angle, a plurality of pressure sensors 86 arranged in the circumferential direction of the air inlet ahead of the inlet guide vane, and a pressure sensor And a guide vane control unit 88 which calculates an optimum installation angle of each inlet guide vane from the output of the compressor to control each actuator, and the guide vane control unit distributes the occurrence of distortion in the circumferential direction upstream of the compressor. In this case, the installation angle of the inlet guide vanes at the generated circumferential position is controlled, and the inflow angle to the compressor rotor blades is kept optimal.
[0007]
[Patent Literature 4] discloses a "pressure control device for a compressor" that includes a guide vane provided at an appropriate position in an air flow path connected to a compressor, and a blown air branched from a discharge side flow path of the compressor. And a blow-off valve interposed in the path,..., Wherein the guide vane and the blow-off valve are selectively opened and closed to maintain the discharge pressure constant.
[0008]
[Patent Document 1]
Japanese Patent Application Laid-Open No. 04-318228 [Patent Document 2]
JP 09-89725 A [Patent Document 3]
JP 2002-130183 A [Patent Document 4]
JP-A-58-35291
[Problems to be solved by the invention]
In order to test engine performance while simulating a high altitude flight state, it is necessary to store an aero engine in a test chamber and reduce the pressure inside the test chamber to an assumed high altitude flight pressure. Therefore, a large amount of exhaust gas exhausted from the engine during the test is exhausted to the outside, and the pressure in the test chamber is reduced to a low pressure close to a vacuum (for example, 1/25 to 1/30 atm) and maintained. An axial compressor having a high pressure ratio (for example, 25 to 30) is used.
[0010]
On the other hand, in the engine performance test, the amount of exhaust gas fluctuates in order to change the load, the number of revolutions, etc. of the engine. Therefore, the axial flow compressor is controlled in accordance with the fluctuation, and the internal pressure is adjusted to a predetermined test. Must be maintained at pressure. Conventionally, such control has been performed by employing a variable stator blade in an axial flow compressor and using both variable stator blade control for controlling the variable vane opening and rotation speed control.
[0011]
However, since high operating accuracy and responsiveness are required for this variable vane mechanism, not only the mechanism of the axial flow compressor becomes complicated, but also the control becomes complicated, and a long-term continuous test is required. In this case, there is a problem that reliability is low.
In other words, in the case of the axial flow compressor, the performance curve (flow-pressure ratio) stands almost vertically, so that a slight flow fluctuation of the suction gas easily leads to a large fluctuation of the pressure ratio. Surge and choke could lead to compressor damage.
[0012]
The present invention has been made to solve the above problems. That is, the present invention uses an axial flow compressor having a simple mechanism that does not require a variable stator blade mechanism, and has a simple configuration and control as a whole, and an internal pressure corresponding to a variation in exhaust gas amount in an engine performance test. It is an object of the present invention to provide a highly reliable high-altitude performance test apparatus capable of precisely maintaining a predetermined test pressure at a predetermined test pressure, having no risk of surge or choke, and performing a continuous test stably for a long time, and a pressure control method therefor.
[0013]
[Means for Solving the Problems]
ADVANTAGE OF THE INVENTION According to this invention, the closed chamber which accommodates an aviation engine inside so that an operation is possible, the exhaust line which exhausts the gas in this closed chamber to the exterior, and which sucks gas from the inside of the closed chamber provided in the exhaust line, and is large. An axial compressor that pressurizes to an atmospheric pressure, an external air supply valve that supplies external air to the inlet side of the axial compressor, and a pressure ratio control that controls the external air supply valve to maintain a constant pressure ratio of the axial compressor. , A high altitude performance test apparatus is provided.
[0014]
Further, according to the present invention, the gas in the closed chamber containing the aviation engine is sucked by the axial compressor, pressurized to the atmospheric pressure and exhausted to the outside, and simultaneously supplied to the inlet side of the axial compressor. A pressure control method for a high altitude performance test apparatus is provided, which controls an outside air flow rate and thereby keeps a pressure ratio of an axial flow compressor constant.
[0015]
According to the above-described apparatus and method of the present invention, instead of adjusting the suction gas flow rate by the axial-flow compressor using a variable stationary blade or the like, the axial-flow compressor operates in a constant operation state, and the input of the axial-flow compressor is controlled. By controlling the flow rate of the outside air supplied to the side and thereby keeping the pressure ratio of the axial compressor constant, the pressure on the inlet side can be kept constant as a result since the atmospheric pressure is constant.
In addition, since the intake gas flow rate (= exhaust gas amount + external air flow rate) of the axial compressor can be kept constant only by controlling the external air flow rate, it can be easily followed even if the exhaust gas amount of the aircraft engine fluctuates. Can be. Therefore, the internal pressure can be maintained at a predetermined test pressure in accordance with the variation of the exhaust gas amount in the engine performance test with a simple configuration and control as a whole.
In addition, since the axial compressor is operated in a constant operating state, there is no possibility of surge or choke, a continuous test can be stably performed for a long time, and reliability can be improved.
[0016]
According to a preferred embodiment of the present invention, an exhaust flow control valve provided downstream of the closed chamber of the exhaust line to control an exhaust flow rate, and the exhaust flow control valve is controlled to keep the pressure of the closed chamber constant. An exhaust flow rate controller, and controls an exhaust flow rate from the closed chamber so as to keep the pressure in the closed chamber constant.
With this configuration and method, the pressure on the outlet side (= the inlet side of the axial compressor) of the exhaust flow rate control valve is kept constant, so that the pressure in the closed chamber can be kept constant with high accuracy. .
[0017]
It is preferable that the outside air supply valve is a hydraulically driven flow control valve. By using a hydraulically driven flow control valve having excellent responsiveness, responsiveness to a change in the amount of exhaust gas can be improved, and controllability can be improved.
[0018]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. In the drawings, common parts are denoted by the same reference numerals.
[0019]
FIG. 1 is an overall configuration diagram showing a first embodiment of the high altitude performance test apparatus of the present invention. In this figure, the high altitude performance test apparatus of the present invention includes a closed chamber 10, an exhaust line 11, an axial compressor 12, an outside air supply valve 14, and a pressure ratio controller 16.
[0020]
The closed chamber 10 stores the aviation engine 1 to be tested inside so as to be operable. On the upstream side (left side in the figure) of the closed chamber 10, an introduction air line (not shown) for supplying air to be introduced into the aviation engine 1 is provided, and air 2 having a predetermined pressure simulating a high altitude flight state is provided by the aviation engine. Flow into 1. On the downstream side of the closed chamber 10, water injection devices 4a and 4b, a heating device 5, a water drop remover 6 and the like are provided to cool the high-temperature exhaust gas 3 discharged from the aircraft engine 1 into the closed chamber 10. It is supposed to.
[0021]
The exhaust line 11 is a piping line that communicates a downstream end (right end in the figure) of the closed chamber 10 with an outside (for example, a stack) not shown, and has a function of exhausting gas in the closed chamber 10 to the outside.
[0022]
The axial compressor 12 is provided in the middle of the exhaust line 11, sucks gas from the inside of the closed chamber 10, and pressurizes the gas to atmospheric pressure. In this example, the axial compressor 12 is driven by the gas turbine 12a, and operates in a predetermined operation state in which a continuous test can be stably performed for a long time without a risk of surge or choke.
[0023]
The outside air supply valve 14 is provided on a piping line connected to the inlet side (suction side) of the axial compressor 12, and has a function of adjusting the amount of outside air supplied to the inlet side of the axial compressor 12. The outside air supply valve 14 is preferably a highly responsive hydraulically driven flow control valve.
[0024]
The pressure ratio controller 16 has pressure detectors 16a and 16b for detecting the pressures P1 and P2 on the inlet side and the outlet side of the axial compressor 12, and performs feedback control of the outside air supply valve 14 to control the axial compressor. The pressure ratio (= P2 / P1) is kept constant.
[0025]
In FIG. 1, the high altitude performance test apparatus of the present invention further includes an exhaust flow rate control valve 18 and an exhaust flow rate controller 20.
The exhaust flow rate adjusting valve 18 is provided immediately downstream of the closed chamber 10 of the exhaust line 11 and adjusts an exhaust flow rate flowing through the exhaust line 11. The exhaust flow controller 20 has a pressure detector 20a for detecting the pressure P0 in the closed chamber 10, and performs feedback control of the exhaust flow control valve to keep the pressure P0 of the closed chamber 10 constant. .
[0026]
Using the above-described apparatus, in the method of the present invention, the gas in the closed chamber 10 containing the aviation engine 1 is sucked by the axial compressor 12, pressurized to the atmospheric pressure, and exhausted to the outside. The flow rate of outside air supplied to the inlet side of the compressor 12 is controlled, and the pressure ratio (P2 / P1) of the axial compressor 12 is kept constant.
Further, the exhaust flow rate from the closed chamber 10 is controlled so that the pressure in the closed chamber 10 is kept constant.
[0027]
FIG. 2 is an operation characteristic diagram of the axial compressor. In this figure, the horizontal axis represents the suction gas flow rate, and the vertical axis represents the compressor pressure ratio (P2 / P1). Lines indicated by A to C in the figure correspond to the stationary blade opening of the compressor.
As shown in this figure, under the condition where the vane opening is fixed, the relationship between the pressure ratio and the suction gas flow rate is 1: 1. It can be seen that maintaining a constant value requires high operating accuracy and responsiveness.
[0028]
On the other hand, in the present invention, the axial compressor 12 operates in a predetermined operating state (operating point) where there is no possibility of surge or choke and a continuous test can be stably performed for a long time.
The suction gas flow rate at the operating point is set to the sum of the amount of exhaust gas from the closed chamber and the outside air flow rate. By adjusting the outside air flow rate, the suction gas flow rate of the compressor is kept constant, and the pressure ratio is controlled to be constant. .
That is, even during the normal test, about 5 to 10% of the outside air of the exhaust gas amount ((1) in the figure) from the closed chamber 10 is drawn from the outside air supply valve 14 ((2) in the figure). By adjusting the outside air flow rate (2 in the figure) by the outside air supply valve 14 in response to the change in the amount of exhaust gas, the fluctuation in the amount of exhaust gas (1 in the figure) from the closed chamber 10 is absorbed and the operation is performed. Control is performed so that the point (pressure ratio) becomes constant.
According to the pressure ratio control of the present invention, the operating point of the compressor can be kept constant during the high altitude performance test, so that the compressor can be operated stably.
[0029]
According to the above-described apparatus and method of the present invention, instead of adjusting the suction gas flow rate by the axial compressor by using a variable vane or the like, the axial compressor 12 is operated in a constant operation state, and the axial compressor is operated. By controlling the outside air flow rate supplied to the inlet side of the compressor and thereby keeping the pressure ratio (P2 / P1) of the axial compressor 12 constant, the atmospheric pressure P2 is constant, and as a result, the pressure on the inlet side is increased. P1 can be kept constant.
Also, the suction gas flow rate (= exhaust gas quantity + outside air flow rate) of the axial compressor can be made constant only by controlling the outside air flow rate (2), so that even if the exhaust gas quantity (1) of the aircraft engine fluctuates. , Can be easily followed. Therefore, the internal pressure can be maintained at a predetermined test pressure in accordance with the variation of the exhaust gas amount in the engine performance test with a simple configuration and control as a whole.
In addition, since the axial compressor is operated in a constant operating state, there is no possibility of surge or choke, a continuous test can be stably performed for a long time, and reliability can be improved.
[0030]
Further, by providing the exhaust flow rate control valve 18 and the exhaust flow rate controller 20, the pressure P1 on the outlet side (= inlet side of the axial flow compressor 12) of the exhaust flow rate control valve 18 is kept constant. The pressure P0 of the closed chamber 10 can be kept constant with high accuracy.
[0031]
FIG. 3 is a partial configuration diagram showing a second embodiment of the high altitude performance test apparatus of the present invention. This figure shows a case where two axial compressors 12b and 12c are operated in parallel.
As shown in this figure, in the case of the parallel operation, only the pressure ratio of one axial compressor 12b is monitored, the external air supply valve 14a of the axial compressor 12b is controlled, and the other axial compressors 12c are controlled. In the outside air supply valve 14b, the pressure ratio control is not performed, and the opening degree is fixed.
[0032]
With this configuration, even when the amount of exhaust gas is large and one axial compressor cannot cope, it can be coped with by parallel operation of two (or three or more) axial compressors. In addition, the pressure ratio control is only one of them, and the other is not controlled. Therefore, the internal pressure is controlled to a predetermined test pressure corresponding to the fluctuation of the exhaust gas amount in the engine performance test with a simple configuration and control as a whole. Can hold.
[0033]
FIG. 4 is a partial configuration diagram showing a third embodiment of the high altitude performance test apparatus of the present invention. This figure shows a case where two axial compressors 12b and 12c are operated in series.
As shown in this figure, in the case of series operation, the total pressure ratio of the two axial compressors 12b and 12c is monitored, and one axial compressor is controlled so that the value becomes a set value. The control is performed only by the outside air supply valve 14 of 12b. Further, the outside air supply valve of the other exhaust compression 14b is fully closed without performing the pressure ratio control in consideration of the controllability and the flow rate balance as a whole of the axial compressor during the series operation.
[0034]
With this configuration, even if the test pressure is close to vacuum and the pressure ratio (P2 / P1) required as a whole is too high to be accommodated by one axial compressor, two (or three or more) shafts This can be handled by the series operation of the flow compressor. In addition, the pressure ratio control is only one of them, and the other is not controlled. Therefore, the internal pressure is controlled to a predetermined test pressure corresponding to the fluctuation of the exhaust gas amount in the engine performance test with a simple configuration and control as a whole. Can hold.
[0035]
It should be noted that the present invention is not limited to the above-described embodiment, and can be variously changed without departing from the gist of the present invention.
[0036]
【The invention's effect】
As described above, the high-altitude performance test apparatus and the pressure control method of the present invention use an axial flow compressor having a simple mechanism that does not require a variable vane mechanism, and have an engine with a simple configuration and control as a whole. The internal pressure can be precisely maintained at a predetermined test pressure in response to the variation in the amount of exhaust gas in the performance test, and there is no possibility of surge or choke, and the reliability can be continuously tested for a long time with high reliability. Has excellent effects.
[Brief description of the drawings]
FIG. 1 is an overall configuration diagram showing a first embodiment of a high altitude performance test apparatus of the present invention.
FIG. 2 is an operation characteristic diagram of the axial compressor.
FIG. 3 is a partial configuration diagram showing a second embodiment of the high altitude performance test apparatus of the present invention.
FIG. 4 is a partial configuration diagram showing a third embodiment of the high altitude performance test apparatus of the present invention.
FIG. 5 is a configuration diagram of a conventional high altitude performance test apparatus.
FIG. 6 is a configuration diagram of another conventional high altitude performance test apparatus.
FIG. 7 is a schematic diagram of conventional pressure control of an axial compressor.
[Explanation of symbols]
1 aviation engine, 2 air, 3 exhaust gas,
4a, 4b water injection device, 5 heating device, 6 water drop remover,
10 closed chamber, 11 exhaust line,
12, 12b, 12c axial compressor, 12a gas turbine,
14, 14a, 14b outside air supply valve (hydraulic drive flow rate control valve),
16 pressure ratio controller, 16a, 16b pressure detector,
18 exhaust flow control valve,
20 Exhaust flow controller, 20a Pressure detector

Claims (5)

A closed chamber that houses the aviation engine operably inside, an exhaust line that exhausts gas in the closed chamber to the outside, and an axial flow that is provided in the exhaust line and sucks gas from the closed chamber and pressurizes it to atmospheric pressure A compressor, an outside air supply valve that supplies outside air to an inlet side of the axial flow compressor, and a pressure ratio controller that controls the outside air supply valve and maintains a constant pressure ratio of the axial flow compressor. High altitude performance test equipment characterized by the following. An exhaust flow rate control valve provided on the downstream side of the closed chamber of the exhaust line to control an exhaust flow rate, and an exhaust flow rate controller that controls the exhaust flow rate control valve to maintain the pressure of the closed chamber constant. The high altitude performance test apparatus according to claim 1, wherein: The high altitude performance test apparatus according to claim 1, wherein the outside air supply valve is a hydraulically driven flow control valve. The gas in the closed chamber containing the aviation engine is suctioned by the axial compressor, pressurized to the atmospheric pressure and exhausted to the outside, and at the same time, the external air flow supplied to the inlet side of the axial compressor is controlled, whereby A pressure control method for a high altitude performance test device, characterized in that a pressure ratio of an axial compressor is kept constant. The pressure control method according to claim 4, wherein an exhaust flow rate from the closed chamber is controlled so as to keep the pressure of the closed chamber constant.

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