RU55468U1 - INFORMATION AND MEASURING CONTROL DEVICE TEMPERATURE SHOVEL TURBINE GAS TURBINE ENGINE - Google Patents

Abstract

The utility model relates to information-measuring technology and can be used for non-contact measurement of the temperature of the turbine blades of a gas turbine engine and temperature control of an aircraft power plant. The problem, which the utility model is aimed at, is to expand the functionality, increase efficiency and reliability. The problem is solved due to the fact that in the information-measuring device for controlling the temperature of the blades of the turbine of a gas turbine engine, containing an optical head, coupled to the input end of the fiber, the output end of which is coupled to a radiation receiver, which is part of the electronic conversion, amplification and signal processing unit , it includes a microcontroller (PIC - controller), a fuel system regulator, a recording device, a digital indicator display and an alarm, an optical lens the head is made with adjustable focal length, and in each stage of the engine an optical head and part of the fiber are placed inside the protective optical probe, the free end of the probe directed to the blades is covered with infrared transparent glass and placed in the turbine housing of the engine, and the other part of the fiber is outside the engine placed inside a protective flexible metal hose, while the number of measurement channels is equal to the number of stages of the engine turbine, the outputs of all measuring channels are connected to mic the controller having a built-in switch, an analog-to-digital converter, input / output ports, memory, and the microcontroller output is connected to the fuel system regulator, a recording device and a digital indicator display and an indicator of excessive temperatures of the turbine as a whole and individual blades located in the cockpit.

In contrast to the prototype, a microcontroller (PIC controller), a fuel system regulator, a recording device, a digital indicator display and an annunciator, an optical head lens are made with adjustable focal length, and an optical head and a part of the optical fiber are placed inside the protective optical fiber in each engine stage of the probe, the free end of the probe directed at the blades is closed by infrared transparent glass and placed in the turbine housing of the engine, and the other part of the optical fiber outside the engine placed inside a protective flexible metal hose, the number of measurement channels being equal to the number of engine turbine stages, the outputs of all measuring channels are connected to a microcontroller having a built-in switch, an analog-to-digital converter, input / output ports, memory, and the microcontroller output is connected to the fuel system regulator, a recording device and a digital indicator display located in the cockpit and an indicator of excessive temperatures of the turbine as a whole and individual blades.

Description

The utility model relates to information-measuring technology and can be used for non-contact measurement of the temperature of the turbine blades of a gas turbine engine and temperature control of an aircraft power plant.

A known device for measuring the temperature of the turbine blades of a gas turbine engine (US patent 4,579,461, class G 01 j 5/32, 1986), in which the optical head is coupled to the input end of the fiber, the output end of which is coupled to the radiation receiver.

Its disadvantage is the relatively low accuracy of temperature measurement, which is why this device cannot be used on new gas turbine engines.

As a prototype, an information-measuring device for monitoring the temperature of the turbine blades of a gas turbine engine (RU, patent, 2032887, CL G 01 J 5/30, 1995) was adopted, containing an optical head coupled to the input end of the fiber, the output end of which is connected to the receiver radiation, which is part of the electronic unit for conversion, amplification and signal processing.

The disadvantages of this device are limited functionality, low efficiency and reliability.

The problem, which the utility model is aimed at, is to expand the functionality, increase efficiency and reliability.

The problem is solved due to the fact that in the information-measuring device for monitoring the temperature of the blades of the turbine of a gas turbine engine, containing an optical head associated with

the input end of the fiber, the output end of which is coupled to the radiation receiver, which is part of the electronic unit for converting, amplifying and processing the signal, unlike the prototype, a microcontroller (PIC controller), a fuel system regulator, a recording device, a digital indicator display are introduced into it and a signaling device, the lens of the optical head is made with adjustable focal length, and in each stage of the engine the optical head and part of the optical fiber are placed inside the protective optical NDA, the free end of the probe directed to the blades is closed with infrared transparent glass and placed in the engine turbine housing, and the other part of the fiber optic cable outside the engine is placed inside a protective flexible metal hose, while the number of measurement channels is equal to the number of stages of the engine turbine, the outputs of all measuring channels are connected with a microcontroller having a built-in switch, an analog-to-digital converter, input / output ports, memory, and the output of the microcontroller is connected to the fuel system regulator, a recording device and a digital indicator display located in the cockpit and an indicator of excessive temperatures of the turbine as a whole and individual blades.

The essence of the utility model is illustrated by drawings. Figure 1 shows a block diagram of an information-measuring control device for the temperature of the turbine blades of a gas turbine engine. Figure 2 shows the installation diagram of the optical probe in the casing of a gas turbine gas turbine engine.

The inventive device contains a fuel system regulator for a gas turbine engine 1, which regulates the supply of fuel (Top) to the combustion chambers of a gas turbine engine (GTE) 2. Air (B) is also supplied to the TBG.

In series with the gas turbine engine, N measuring channels are included (according to the number of stages of the gas turbine turbine), consisting of chains with optical heads 3-1, 3-2, ..., 3-N, coupled to the input ends of the optical fibers 4-1, 4-2 , ..., 4-N. The output ends of the optical fibers are paired with

radiation receivers, which are part of the electronic units for conversion, amplification and signal processing 5-1, 5-2, ... 5-N.

Thanks to fiber optic fibers several meters long, the electronic components are removed at a certain distance from the high-temperature zones of the gas turbine engine.

The outputs of the electronic units are connected to a microcontroller (PIC controller) having a built-in switch, an analog-to-digital converter, input-output ports, and memory.

The output of the microcontroller 6 is electrically connected with the regulator of the fuel system of the turbine engine 1, as well as with a black box recorder 7, which records the temperature information of the blades of all stages of the turbine engine.

In the cockpit there is a digital indicator display 8 and an alarm 9 about excessive temperatures of the turbine as a whole and individual blades, the information on which the microcontroller issues.

In FIG. 2 shows a diagram of an optical probe installation in a gas turbine gas turbine housing. The optical probe is made in the form of coaxial tubes 1 and 2 of different diameters, hermetically fastened to each other and placed between the outer 3 and inner 4 casings of the gas turbine. Couplings 5 and 6 are designed for mounting. Outside the outer casing of the gas turbine, the tube 2 is fastened with a flexible metal hose. A flexible optical fiber 8 is placed inside the metal sleeve and tubes. The free end of the optical probe directed to the blades 9 is closed by an infrared transparent glass 10 and placed inside the gas turbine 4. The inside of the optical probe is placed between the protective infrared transparent glass 10 and the input end of the optical fiber 8 lens 11 with an adjustable focal length, allowing you to adjust the diameter of the spot of sight. The lens simultaneously performs the functions of a bandpass filter of frequencies.

The inventive information-measuring control device temperature of the turbine blades of the turbine engine is as follows.

The radiation from the blades 9 (Fig. 2) is projected by the optical head through an infrared transparent glass 10 and a focusing lens 11 onto the input end of the fiber 8.

This picture of the signal conversion takes place in each of the N measuring channels corresponding to the stages of the turbine engine (figure 1).

From the output ends of the optical fibers 4-1, 4-2, ..., 4-N, the optical radiation is supplied to the respective radiation receivers, which are part of the electronic conversion, amplification and signal processing units 5-1, 5-2, ... 5-N. Next, the signals are fed to the microcontroller 6.

In the microcontroller 6, the input signals are fed to a multi-channel switch, which commutes the analog signals of electronic blocks 5-1, 5-2, ..., 5-N. Further, after the switches, the signal is amplified by an amplifier, converted into a digital form in an analog-to-digital converter, and enters the memory block, where it is processed. Through the I / O ports, the microcontroller 6 is connected to external devices, issuing a control signal to the fuel system regulator 1, which controls the operation mode of the gas turbine engine. Through the I / O ports, the microcontroller 6 provides information on the temperature of the blades of all stages of the turbine engine, which is recorded by a black-box recorder 7. Similarly, the microcontroller is connected to a digital indicator display 8 located in the cockpit, which displays the temperature of the blades of all stages of the turbine engine, and an alarm 9 about the excessive temperatures of the turbine as a whole and individual blades.

Thus, the introduction of a microcontroller (PIC controller), a fuel system regulator, a recording device, a digital indicator display and an annunciator, the implementation of an optical head lens with adjustable focal length, and the placement of an optical head and part of a fiber waveguide inside each optical engine probe in each stage of the engine functionality of the claimed device.

Placing a protective optical probe in the turbine housing of the engine, the free end of which, directed to the working blades, is covered by infrared transparent glass and placing inside the protective flexible metal sleeve of another part of the fiber optic cable outside the engine can improve reliability.

Measuring the temperature of the turbine blades of a gas turbine engine through N channels, the number of which is equal to the number of stages of the engine turbine, connecting the outputs of all measuring channels to a microcontroller having a built-in switch, an analog-to-digital converter, input / output ports, memory, and connecting the output of the microcontroller to the fuel system regulator , with a recording device and a digital indicator display and a signaling device about excessive temperatures of the turbine as a whole and individual blades located in the cockpit is to increase the efficiency of the disclosed device.

Claims (1)

Information-measuring control device for the temperature of the turbine blades of a gas turbine engine, containing an optical head coupled to the input end of the fiber, the output end of which is coupled to a radiation receiver, which is part of the electronic unit for converting, amplifying and processing the signal, characterized in that a microcontroller is inserted into it , fuel system regulator, recording device, digital indicator display and signaling device, optical head lens made with adjustable focus at each stage of the engine, the optical head and part of the fiber are placed inside the protective optical probe, the free end of the probe directed to the blades is covered by infrared transparent glass and placed in the turbine housing of the engine, and the other part of the fiber outside the engine is placed inside the protective flexible a metal hose, while the number of measurement channels is equal to the number of stages of the engine turbine, the outputs of all measuring channels are connected to a microcontroller with built-in a mutator, an analog-to-digital converter, input / output ports, memory, and the output of the microcontroller is connected to the fuel system regulator, a recording device and a digital indicator display and an indicator of critical temperatures of the turbine as a whole and individual blades located in the cockpit.