JPH02185627A - Device for controlling two-shaft gas turbine - Google Patents

Abstract

PURPOSE:To enable traveling even at the time of failure of the inlet temperature sensor of a combustor by controlling a fuel flow rate in accordance with the output of an intake air temperature correcting means for correcting an intake air temperature to be a defined value and outputting same only when the intake air temperature into the combustor is out of a defined range. CONSTITUTION:A gas generator GG is driven by a combustion gas from a combustor CC and compresses an intake air fed into the combustor CC while feeding a combustion gas into an output turbine PT via a variable nozzle VN to drive same. By detecting the temperature of an intake air fed into the combustor CC, it is judged whether the intake air temperature is within a defined range or not by a judging means 1. When within the defined range, a correcting means 2 does not carry out the correction of the intake air temperature but a control means 3 obtains a fuel flow rate based on the detected intake air temperature and air flow rate. On the other hand, when not within the defined range, i.e., at the time of the failure of the intake air sensor, a fuel flow rate is operated and controlled based on the corrected value set by the correcting means 2. Thereby, a vehicle can safely travel even at the time of the failure of the sensor.

Description

[Detailed Description of the Invention] [Field of Industrial Application] The present invention relates to a control device for a two-shaft gas turbine engine, and in particular, to a control device for a two-shaft gas turbine engine that can prevent the engine from being damaged even when an abnormality occurs in the intake air temperature sensor of the two-shaft gas turbine engine. The present invention relates to a control device that can control fuel.

[Conventional technology]

Two-shaft gas turbine engines are (1) rotary motion only, so they can run at high speeds continuously with low vibration; (2) they are continuous combustion engines, so they can use a wide variety of fuels, including gasoline, diesel oil, kerosene, and methanol. (3) It has torque characteristics suitable for automobiles, such as large low-speed torque, so its practical use as an automobile engine has been considered in recent years.

FIG. 4 shows an example of a general configuration of a conventional two-wheel gas turbine engine mounted on an automobile with an automatic transmission.

In the figure, C is a compressor, II8 is a heat exchanger, C
C is a combustor, and CT is a compressor turbine. The compressor C and the compressor turbine CT are directly connected through a rotating shaft, and fuel is supplied to the combustor CC via an actuator ^l. Intake air (hereinafter referred to as intake air) is compressed by a compressor C, heated by a heat exchanger HB, mixed with fuel and combusted in a combustor CC, and the combustion gas rotates a compressor turbine CT. The compressor turbine CT and the compressor C may be collectively referred to as a gas generator 6G, and the rotation speed of the compressor turbine CT determines the degree of compression of the compressor C. The combustion gas that has driven the compressor turbine CT passes through a variable nozzle VN adjusted by an actuator ^2, drives a power turbine (output turbine) PT, and then passes through a heat exchanger HE to become exhaust gas and is discharged to the atmosphere.

The above is the configuration of the two-shaft gas turbine GT. The rotation of the power turbine PT is decelerated by the reduction gear R/G and transmitted to the automatic transmission A/T, and after being converted to a rotation speed according to the shift state, the rotation speed is It is transmitted to the wheels W via a moving gear.

Note that the actuator ^1 supplies fuel to the combustor CC according to a command from the control circuit C0NT, and the actuator A2 adjusts the opening degree of the variable nozzle VN according to a command from the control circuit C0NT. The opening degree of the accelerator pedal and engine operating state parameters from a sensor (not shown) are input to this control circuit C port NT.
is the actuator ^1 depending on the operating condition of the engine. Drive ^2.

In addition, in general, the subscripts attached to the intake pressure P and temperature T are the numbers surrounded by circles, such as P3 for the intake pressure at the position of ■ in Figure 4, and T for the temperature at the position of ■. It shows the intake pressure P and temperature T at the position, the rotation speed of the rotating shaft of the gas generator GG is expressed as N1, and the rotation speed of the output shaft of the power turbine PT via the reduction gear fl/G is expressed as N.

In the two-shaft gas turbine engine configured as described above, the accelerated flow of the gas generator GG and the fuel control within a certain predetermined time after the gas generator 6G shifts to a steady state are controlled by the outlet temperature of the combustor CC. The applicant has already proposed a device based on T.
(See No. 47). The fuel control in this control device is based on the target value T4S1 of the intake air outlet pressure P3 of the compressor C and the intake air temperature of the compressor turbine CT! ? The intake air flow rate Ga is calculated from the calculated air flow rate Ga and the target value of the inlet temperature T 4 S II ? The fuel flow rate Gf supplied to the engine is calculated from the actually measured inlet temperature T35 of the intake air of the combustor CC.

[Problem to be solved by the invention]

However, since this control device measures the inlet temperature Tss of the combustor CC of the gas turbine engine using a thermocouple or the like as a temperature sensor, when the thermocouple is disconnected, the fuel flow 1
There is a problem that calculation of 1Gf becomes impossible and fuel control becomes impossible. The reason for this will be explained below.

The intake air temperature T4 of the compressor turbine CT of the gas turbine engine is calculated by the following formula, where K is a constant, Gf is the fuel flow rate, 6a is the air flow rate, and 'I'35 is the inlet temperature of the combustor CC.
is required.

T4 = K −Gf/Ga+ 'r, s+HH-H■
The inlet temperature T of the compressor turbine CT is the highest temperature in the engine, and in fuel control of a gas turbine engine, how to use this temperature T near the maximum allowable temperature is important for the thermal efficiency of the engine. . For this reason, combustor C
The inlet temperature T35 of C occupies an important element in Equation 0. Therefore, when the thermocouple for detecting the inlet temperature T35 of the combustor CC is disconnected, the detected value will be (a) 0, depending on the circuit configuration of the detection circuit, or (c)
There are two possible cases in which a large value that is not normally possible is shown.

In the case of (a), the term T'35 in equation 0 will have a small value, so the fuel flow rate Gf will increase, the actual population temperature T4 of the compressor turbine CT will rise, and in the worst case, the engine may be damaged. invite On the other hand, in case (c), the term Tss in equation 0 becomes large, so the fuel flow lGf decreases, making it impossible to operate the engine. In this way, (a)
, (6) In either case, a vehicle equipped with a gas turbine engine becomes unable to run.

The present invention solves this problem of the two-shaft gas turbine engine by making the inlet temperature T35 of the combustor CC a fixed constant when the sensor for determining the inlet temperature T35 of the combustor CC breaks down. An object of the present invention is to provide a control device for a two-shaft gas turbine engine that allows the engine to run without stopping.

[Means to solve the problem]

As shown in FIG. 1, the two-shaft gas turbine engine of the present invention that achieves the above object includes a gas generator GG that is driven by combustion gas from the combustor CC to compress intake air into the combustor CC; An output turbine PT driven by combustion gas from the gas generator GG to drive a load, means for detecting the intake air temperature Ls to the combustor CC, means for determining the compressor outlet air flow rate Ga, and the intake air temperature 735. A control device for a two-shaft gas turbine engine, comprising means for calculating a fuel flow rate from an air flow rate Ga,
an intake air temperature determining means 1 for determining whether the intake air temperature T35 to the combustor CC is within a predetermined range; and when the intake air temperature 'Ls is outside the predetermined range, the intake air temperature T+ is determined;
an intake air temperature correction means 2 that corrects s to a predetermined value and outputs it, and does not perform correction at other times; and this intake air temperature correction means 2.
The fuel flow rate control means 3 controls the fuel flow rate Gf according to the output from the fuel flow rate control means 3.

[For production]

According to the control device for a two-shaft gas turbine engine of the present invention,
In a vehicle equipped with a two-shaft gas turbine engine, if the detected intake air temperature Ls to the combustor CC is within a predetermined range, the fuel flow rate Gf is calculated based on that value, and the detected intake air temperature 'I If ``35'' is not within the predetermined range, the fuel flow rate Gf is calculated based on a correction value that replaces that value.

〔Example〕

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

FIG. 2 shows the configuration of an embodiment of a two-shaft gas turbine engine of the present invention installed in a vehicle with an automatic transmission, and shows the same components as the two-shaft gas turbine engine shown in FIG. The same reference numerals (symbols) are given for the above.

In the figure, GT is a gas turbine, and this gas turbine GT includes a front gear F/G to which a fuel pump, an oil pump, a starter motor, etc. are connected, and a compressor C1.
Heat exchanger HE, combustor cc, compressor turbine CT directly connected to compressor C by a rotating shaft, variable nozzle VN
, power turbine (output turbine) PT and reduction gear R/
There are G, etc. Note that the compressor C and compressor turbine CT are referred to as a gas generator 6G.

Intake air is compressed by a compressor C, heated by a heat exchanger H6, mixed with fuel and combusted in a combustor CC, and the combustion gas rotates a compressor turbine CT.

The combustion gas that has driven the compressor turbine CT passes through the variable nozzle VN and drives the power turbine PT, and then passes through the heat exchanger 11ε and is discharged into the atmosphere as exhaust gas.

A1 is an actuator that supplies fuel to the combustor cc;
2. Adjust the opening α of the variable nozzle VN! It is an actuator that

An automatic transmission /T is connected to the reduction gear 1t/G of the gas turbine GT, and the rotation of the power turbine PT of the gas turbine GT is reduced by the reduction gear R/G and transferred to the torque converter of the automatic transmission ^/T. The signal is transmitted to the transmission mechanism T via the T/C, and converted to a rotational speed according to the shift state, resulting in an axle drive output. Furthermore, this torque converter T
/C is provided with a lock-up clutch L/C.

The control circuit IO that controls the gas turbine GT and the automatic transmission A/T includes an input interface INa for analog signals and a manual interface INd for digital signals.
, /D to an analog-to-digital converter that digitally converts the signal from the input interface INa.

Central processing unit cpu, random access memory R
AM, a read-only memory IJROM, and an output circuit OUT, which are connected to each other by a pass line 11.

In addition, a gas generator 6 is used for a two-shaft gas turbine engine.
A rotation speed sensor SN, which detects the rotation speed N, of G.

Temperature sensor s that detects the outlet temperature T of the compressor C
'rs, a temperature sensor 5Tss that detects the outlet temperature Tss of the heat exchanger HH, a temperature sensor ST that detects the outlet temperature of the power turbine PT, a rotational speed that detects the rotational speed N3 of the gas turbine GT that has passed through the reduction gear R/G. Rotation speed sensor SNF that detects sensor SN3° and axle drive rotation speed Np
etc. are provided.

The analog signal input interface INa receives the signal N1 from the sensor described above. Na, Np, P3
．． T35.

Analog signals from Ts and the accelerator pedal are input, and digital signals such as on/off signals from the key switch, shift position signals from the shift lever, and brake signals from the brake are input to the human input interface INd for digital signals. .

On the other hand, from the output circuit OUT, a signal Gf instructs the fuel flow rate to the actuator ^1 of the combustor CC.

Signal that instructs actuator ^2 to open the variable nozzle VN αSsF Signal that instructs on/off of lock-up clutch L/C of torque converter T/C 33% Shift signals Sl and S2 of transmission mechanism T and throttle wire signal θ
TII etc. are output.

In the two-shaft gas turbine engine configured as above, normal engine operating conditions! Temperature sensor 5T3 detects the outlet temperature 735 of the heat exchanger HE in I4 (state where the rotation speed of the gas generator GG is higher than the idle rotation speed)
In order to detect the abnormality of sensor 5Tss, the detection value T of sensor 5Tss is
The heat exchanger HE was actually detected using a temperature sensor such as a thermocouple by setting impossible lower and upper limits of 35'.
When the outlet temperature T'as is outside the range between the lower limit value and the upper limit value, it is determined that the temperature sensor 5T35 has failed.

By the way, as mentioned before, the artificial temperature T4 of the compressor turbine CT is given by the following equation (2).

T4 =K - Gf/Ga 10T35 ”...”■In this formula 0, if the value of T'35 is increased, the fuel flow rate Gf will decrease, which will hinder engine operation, and T35 When the value of is decreased, the fuel flow lGf increases and the actual inlet temperature T of the compressor turbine CT
, may rise and cause damage to the engine.

Therefore, in the control device for a two-shaft gas turbine engine of the present invention, when the temperature sensor 5T35 is abnormal, the detected value T35' from the temperature sensor 5T35 is converted to the outlet temperature Tss of the heat exchanger function in the actual operating state of the engine. By correcting to the upper limit of , it is possible for vehicles equipped with gas turbine engines to run without stopping. Since such control is actually performed by the control circuit 10, the operation of the control circuit 10 when the temperature sensor 5T35 is normal and when it is abnormal will be described next using the flowchart in FIG.

In step 301, the operating state parameters of the engine are manually input to the control circuit IO. These operating state parameters include, for example, the rotational speed N1 of the gas generator G6, the accelerator opening degree θ, C, the outlet temperature T6 of the compressor turbine PT, and the detected value 'r3 of the outlet temperature Tss of the heat exchanger ■ε.
5', the outlet pressure P3 of the compressor C, the input rotation speed N3 of the /T to the automatic transmission, etc.

In step 302, the rotation speed N1 of the gas generator GG is
It is determined whether or not is equal to or higher than a set rotational speed near the idle rotational speed, for example, the idle rotational speed (Nsdt*-ΔN). Note that here, ΔN is l of the idle rotation speed N1dL.
The value is approximately 0%. If the rotation speed N+ of the gas generator 6G is (N1dt*-ΔN) or more (YES)
), the process advances to step 303 and thereafter the temperature sensor 5T35
The detected value T35' of the inlet temperature T35 of the combustor CC from
is normal or not, but the rotation speed N+ is (N
, dL, -ΔN) (N entries), this determination is not made. That is, if Nr<Ntdt*-ΔN, the process proceeds to step 306, where the current detection value 738' from the temperature sensor 5T35 is set as the outlet temperature T35 of the heat exchanger +113, and the process proceeds to step 307.

On the other hand, N,≧N,d,. In step 303, which proceeds when -ΔN, first the detected value T from the temperature sensor 5T35 is
3. It is determined whether or not ° is greater than or equal to the upper limit of the outlet temperature T of the heat exchanger HE, T35- (= 600°C). If T35'< 600°C, the process proceeds to step 304. , Here, it is determined whether or not the detected value T35' from the temperature sensor s'rzs is less than the lower limit value 'rjs-, (= 150°C) of the outlet temperature 735 of the heat exchanger Hε.Step 303 and step 304
When it is determined that 150°C≦'rss' 5600°C (NO in both steps 303 and 304), the process proceeds to step 306, where the detected value T35' from the temperature sensor 5Tjs is considered to be normal and this value is is set to the outlet temperature of the heat exchanger HB, T3°, and the process proceeds to step 307. On the other hand, in step 303 'rss' ≧
When it is determined that the temperature is 600°C, or when it is determined that T3%'< 150°C in step 304, the detected value T35' from the temperature sensor 5T35 is considered to be abnormal, and the process proceeds to step 305, where the gas To operate the turbine engine safely, the outlet temperature of heat exchanger H8 T'as
is set to a correction value, that is, an upper limit value of 600° C., and the process proceeds to step 307.

In step 307, step 305 or step 30
The fuel flow rate Gf is calculated based on the outlet temperature T"ss of the heat exchanger Hε set in step 6. As described above, this calculation is performed based on the outlet pressure P of the intake air of the compressor C and the intake air of the compressor turbine CT. Target value of inlet temperature T 4 S
The intake air flow 11 Ga is determined from e t, and the engine This is to calculate the fuel flow lGf to be supplied to. After this, step 3
In step 08, the time is adjusted by a predetermined cycle time, and after the time adjustment, the process returns to step 301 and the above-described control is repeated.

As described above, in the control device for a two-shaft gas turbine engine of the present invention, conventionally, the detected value of the temperature sensor 5T35 provided at the intake inlet to the combustor CC is directly used as the inlet temperature T'ss of the combustor CC. In contrast to the calculation of the fuel flow lGf, the temperature sensor 5Tzs,
Even in the event of a breakdown, the fail-safe system allows the engine to operate without any problems.

〔Effect of the invention〕

As explained above, according to the control device for a two-shaft gas turbine engine of the present invention, even if the sensor for determining the inlet temperature T35 of the combustor CC fails, the detected value of the sensor is corrected and the fuel Since the flow rate is calculated, there is no risk of damage to the engine, and there is an effect that the vehicle can be driven without stopping.

[Brief explanation of the drawing]

FIG. 1 is a block diagram showing the configuration of the present invention, FIG. 2 is an overall schematic diagram showing the configuration of the control device for a two-wheeled gas turbine engine of the present invention, and FIG. 3 is a diagram showing the control procedure of the control circuit in FIG. FIG. 4 is a schematic flowchart showing the general configuration of a conventional two-shaft gas turbine engine. DESCRIPTION OF SYMBOLS 1... Intake air temperature determination means, 2... Intake air temperature correction means, 3... Fuel flow rate control means, 10... Control circuit, C
...Compressor, CC...Combustor, CT...Compressor turbine, HE...Heat exchanger, PT...
Power turbine, SN,, SN,. SN, ... rotation speed sensor, ST,, ST,,, S
T...Temperature sensor, VN...Variable nozzle. 1st

Claims (1)

[Claims] The combustor (CC) is driven by combustion gas from the combustor (CC).
a gas generator (GG) that compresses the intake air to C);
An output turbine (PT) that is driven by the combustion gas from the gas generator (GG) to drive a load, a means for detecting the intake air temperature (T_3_5) to the combustor (CC), and a compressor outlet air flow rate (Ga ), and a means for calculating a fuel flow rate from these intake air temperature (T_3_5) and air flow rate (Ga), the control device for a two-shaft gas turbine engine comprising: Intake air temperature determination means (1) that determines whether the intake air temperature (T_3_5) is within a predetermined range
and intake air temperature correction means (2) which corrects and outputs the intake air temperature (T_3_5) to a predetermined value when the intake air temperature (T_3_5) is outside the predetermined range, and does not perform correction at other times. A control device for a two-shaft gas turbine engine, comprising: and a fuel flow rate control means (3) that controls a fuel flow rate (Gf) according to the output from the intake air temperature correction means (2).