JPH0628041A - Device for testing exhaust temperature control device - Google Patents

Abstract

PURPOSE:To execute the characteristic test of an exhaust temperature control device built in a gas turbine engine for an aircraft on ground. CONSTITUTION:The exhaust temperature control device 20 inputs an engine rotational frequency simulation signal E from a control alternator 11 and inputs an exhaust gas temperature simulation signal T from a DC voltage generator 14. A personal computer 15 controls a resistor controller 13 to change the rotational frequency of a motor 12 and control the frequency of the signal E and controls the generator 14 so as to control the value of the signal T. An output signal from the device 20 is processed by the personal computer 15 to judge the characteristics of the device 20.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an exhaust temperature control device testing apparatus, which enables a characteristic test of an exhaust temperature control device provided in a gas turbine engine for an aircraft to be easily executed on the ground. Is.

[0002]

2. Description of the Related Art An aircraft gas turbine engine is equipped with an exhaust temperature control device (TEMP AMP). This exhaust temperature control device determines whether the exhaust temperature is appropriate for the engine speed when an engine speed signal indicating the engine speed and an exhaust gas temperature signal indicating the exhaust temperature of the engine are input. When the exhaust gas temperature is not appropriate for the engine speed, it has a function of issuing a correction signal to control the exhaust gas temperature to be normal.

Conventionally, the test for confirming the performance of the exhaust temperature control device cannot be carried out on the ground, and it has been carried out when the altitude reaches from 20,000 feet to 40,000 feet. In this test, it is checked whether the exhaust temperature is within the specified value with respect to the engine speed. And
This confirmation test is performed with the engine output at maximum and the throttle position at the required position.

The reason why the performance test of the exhaust gas temperature control device could not be performed on the ground in the past is as follows. That is, the engine speed of a gas turbine engine for an aircraft changes depending on the engine intake temperature (air density), but it is not possible to create the same environment on the ground as the altitude of 20,000 to 40,000 feet. .

[0005]

As described above, conventionally, the performance test of the exhaust gas temperature control device cannot be performed on the ground, and must be performed when the flight reaches a required altitude. It was Therefore, the performance test cannot be easily performed, and it took a long time to develop the aircraft engine and complete the product.

In view of the above-mentioned conventional technique, it is an object of the present invention to provide a test device capable of performing a performance test of an exhaust gas temperature control device provided in a gas turbine engine for an aircraft on the ground.

[0007]

SUMMARY OF THE INVENTION The structure of the present invention for solving the above-mentioned problems is an engine speed model that simulates an engine speed signal output from a gas turbine engine when an aircraft gas turbine engine is driven. A control alternator that supplies pseudo signals and power source power to an exhaust temperature control device provided in the gas turbine engine, and a motor that rotationally drives the control alternator,
A direct-current voltage generator that supplies an exhaust gas temperature simulation signal that simulates the exhaust gas temperature signal output from the gas turbine engine when the gas turbine engine is driven to the exhaust gas temperature control device, and is preset. According to a schedule, the operation of the motor and the DC voltage generator is controlled so that the frequency of the engine speed pseudo signal and the value of the exhaust gas temperature pseudo signal are changed, and the exhaust temperature control is performed. And a control unit that processes an output signal of the device and determines a signal characteristic thereof.

[0008]

In the present invention, the frequency of the engine speed pseudo signal output from the control alternator and the value of the exhaust gas temperature pseudo signal output from the DC voltage generator are changed according to the program by the control of the control unit. The output signal output from the exhaust temperature control device is processed by the control unit, and the performance of the exhaust temperature control device can be inspected.

[0009]

Embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 is a block diagram showing an embodiment of the present invention,
FIG. 2 is a block diagram thereof. As shown in both figures, the test apparatus 10 of the embodiment includes a control alternator 11 and
It is composed of a motor 12, a resistance controller 13, a DC voltage generator 14, and a personal computer 15. And the exhaust temperature control device (TEMP AMP) 20 which is the test piece
Is unloaded from the gas turbine engine of the aircraft. The control alternator 11 and the DC voltage generator 14 are connected to the control device 20, and the output signal of the exhaust temperature control device 20 is sent to the personal computer 15. ing.

The control alternator 11 generates an engine speed simulation signal E by driving the motor 12 and sends this signal E to the exhaust temperature control device 20. The control alternator 11 also functions as a power source for the exhaust temperature control device 20, and also supplies necessary power source power.

The rotation speed of the motor 12 is the resistance controller 1
It can be changed by changing the resistance value of No. 3, and the resistance value of the resistance controller 13 can be controlled by a command from the personal computer 15. Therefore, when the resistance value of the resistance controller 13 is changed by a command from the personal computer 15, the rotation speed of the motor 12 changes, and the control alternator 11
The frequency of the engine speed pseudo signal E output from
z] can be changed. The personal computer 15 uses the program to set the engine speed pseudo signal E as determined in advance.
Resistor controller 13 so that the frequency of
Issue a command to. Instead of the control alternator 11, a frequency generator or the like may be used to generate the engine speed simulation signal E. In that case, the power supply device of the control device 20 must be prepared separately from the frequency generator.

The motor 12 is a general-purpose motor and has a maximum speed of 12,000 [RPM], which is considerably high speed. Therefore, in order to improve the stability during high-speed rotation, a program for stabilizing the motor rotation speed is added to the control program set in the personal computer 15. Therefore, the motor 12
Can be stably rotated at high speed, and the engine speed pseudo signal E output from the control alternator 11 is equivalent to the engine speed signal generated when the gas turbine engine actually operates.

On the other hand, the DC voltage generator 14 sends to the exhaust temperature control device 20 an exhaust gas temperature simulation signal T in which the voltage value [mv] changes according to a command from the personal computer 15 operating according to the program. Exhaust gas temperature simulated signal T is
It is equivalent to the exhaust gas temperature signal that occurs when the gas turbine engine actually operates.

Exhaust gas temperature control device 20, when receiving engine speed pseudo signal E and exhaust gas temperature pseudo signal T, generates a correction signal (current signal mA). This correction signal is data-processed by the personal computer 15, and the processing result is displayed on the display 15a. The performance of the exhaust temperature control device 20 can be determined by visually observing the projected data with a human. FIG. 3 shows the display 15
An example of the correction signal shown in a is shown.

FIG. 4 shows a flow chart for executing the above control. It should be noted that F1 to F8 in the figure indicate each step of the flowchart. This control is executed seven times in total while changing the engine speed and the exhaust temperature so as to meet the specification instruction.

Referring to FIG. 4, control starts at F1 and the engine speed is input at F2. The resistance of the motor 2 is converted to control the rotation speed until the rotation speed stabilizes within the allowable error of the specification instruction (F3). When the engine speed falls within the tolerance, the exhaust temperature is simultaneously input to the exhaust temperature control device (TEMP AMP) 20 (F
4). When the engine speed and exhaust temperature are input, TEM
The output of PAMP20 is recorded in the personal computer 15 (F
5). The measurement of the TEMP AMP output is executed 7 times while changing the engine speed and the exhaust temperature. Therefore, if it is less than 7 times, the setting of the engine speed and the exhaust temperature is changed (F6), and the control returns to F2 and the control is performed. Repeated. When seven measurements are completed, the measurement result is output on the screen (F
7). A pass / fail judgment is made on the screen (by visual inspection) and the process ends (F8).

The actual operating procedure will be described with reference to FIGS. 1 and 2. TEM unloaded from aircraft engine
The PAMP 20 and the test apparatus 10 are connected. Insert the TEMP AMP test disk into the personal computer 15 and start up. When "T5-N schedule" on the menu display is selected, the simulated signals E and T of the engine speed and the exhaust temperature are input to the TEMP AMP 20. After that, the simulated signals E and T of the engine speed and the exhaust temperature are automatically and sequentially input to the TEMP AMP 20 as required by the specifications. The output of TEMP AMP 20 is recorded each time. When the input of the engine speed and the exhaust temperature pseudo signal according to the specification request is completed, the output value of the TEMP AMP 20 becomes a graph and is output on the screen of the personal computer 15. At this time, if the output of TEMPAMP20 is within the specified value, TEM
The function of PAMP20 is determined to be normal. Like this, T
The performance of the EMP AMP 20 can be confirmed.

Further, in this embodiment, since the motor rotation speed stabilizing program is added, the performance test can be performed with substantially the same accuracy as when the performance test is performed by actually driving the turbine engine in the sky.

[0019]

As described above in detail with reference to the embodiments, according to the present invention, the following effects can be obtained. 1) The control characteristics of the exhaust temperature control device due to changes in the engine speed can be visually confirmed on the ground. 2) The amount of adjustment of the exhaust gas temperature control device can be quantified. 3) Labor saving can be realized, and in the past, four persons were required, but if the present invention is used, only one person is required. 4) The time required for checking the performance of the exhaust gas temperature control device has been shortened.
It only takes minutes.

[Brief description of drawings]

FIG. 1 is a configuration diagram showing an embodiment of the present invention.

FIG. 2 is a block diagram showing an embodiment of the present invention.

FIG. 3 is an explanatory diagram showing an example of a correction signal characteristic of the exhaust temperature control device.

FIG. 4 is a flowchart showing the operation of the embodiment.

[Explanation of symbols]

 10 Test Equipment 11 Control Alternator 12 Motor 13 Resistance Controller 14 DC Voltage Generator 15 Personal Computer 15a Display 20 Exhaust Temperature Control Device E Engine Rotation Speed Simulated Signal T Exhaust Gas Temperature Simulated Signal

Claims (1)

[Claims] 1. An exhaust gas provided to the gas turbine engine, wherein an engine speed simulated signal and a power source power, which simulate an engine speed signal output from the gas turbine engine when the gas turbine engine for an aircraft is driven, are provided. A control alternator supplied to a temperature control device, a motor that rotationally drives the control alternator, and an exhaust gas temperature simulated signal that simulates an exhaust gas temperature signal output from the gas turbine engine when the gas turbine engine is driven. A DC voltage generator to be supplied to the exhaust temperature control device, and to change the frequency of the engine speed pseudo signal and the value of the exhaust gas pseudo signal according to a preset schedule. Controlling the operation of the motor and the DC voltage generator, An exhaust temperature control device testing apparatus, comprising: a control unit that processes an output signal of the exhaust temperature control device and determines a signal characteristic thereof.