JP3161179B2 - Ceramic turbine rotor breakdown detection device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ceramic turbine rotor breakdown detecting apparatus.

[0002]

2. Description of the Related Art In a gas turbine, air compressed by a compressor is heated by a heat exchanger, then mixed and burned with fuel in a combustor, and blown as high-temperature combustion gas to a turbine rotor to rotate at high speed. This is a device that takes out the power to the outside through the output shaft, and has the advantage that there is no major restriction on the properties of the fuel in principle because continuous combustion can be performed. It is expected to improve thermal efficiency.

Here, as a method of inspecting the durability of a ceramic turbine rotor and studying the mechanism of failure,
Conventionally, a cold spin test and a hot spin test are performed.

[0004] The cold spin test is a test in which only a ceramic turbine rotor is rotated without blowing combustion gas in a vacuum chamber, and the hot spin test is performed by actually blowing combustion gas to a ceramic turbine rotor. This is a test for rotating a ceramic turbine rotor at high speed. The cold spin test is performed in a vacuum chamber because the ceramic turbine rotor does not rotate at high speed in air.

Conventionally, in a cold spin test,
Utilizing the phenomenon that ceramic emits light immediately before it is destroyed by high stress, the light emission is detected by a photodetector such as a photodiode, and a high-speed camera is used to photograph the mechanism by which the ceramic turbine rotor is destroyed.

[0006]

However, in the hot spin test, since the combustion gas is actually blown to the ceramic turbine rotor, the ceramic turbine rotor always emits incandescent light. Therefore, in the hot spin test, it is an emission phenomenon immediately before the ceramic turbine rotor breaks due to high stress, or whether the ceramic turbine rotor emits incandescent light simply because of the high temperature when the combustion gas is blown. Identification was difficult.

For this reason, in a hot spin test, an attempt is made to detect the moment of destruction of the ceramic turbine rotor by detecting the light emission phenomenon of the ceramic. However, it has been difficult to accurately detect the moment of destruction of the ceramic turbine rotor. 3-29
No. 760). The present invention has been made in view of the above prior art, and in a hot spin test, instead of detecting a light emission phenomenon immediately before the breakdown of a ceramic as a light emission phenomenon, by detecting the light emission phenomenon as a temperature change,
An object of the present invention is to provide a ceramic turbine rotor destruction detection device capable of detecting a destruction with good responsiveness.

[0008]

According to a first aspect of the present invention which achieves the above object, the amplitude of a specific wavelength range of light emitted from a ceramic turbine rotor immediately before destruction is converted into an energy. A radiation thermometer that detects the temperature of the ceramic turbine rotor at an ultra-high speed, a combustor that blows combustion gas to the ceramic turbine rotor, and the condition that the temperature detected by the radiation thermometer exceeds an upper limit value, A data processing device for emergency stop of the combustor.

According to a second aspect of the present invention, which achieves the above object, the amplitude of a specific wavelength range of light emitted from a ceramic turbine rotor immediately before destruction is converted into an energy amount, and the temperature of the ceramic turbine rotor is set as an ultra-high temperature. A radiation thermometer for detecting at high speed, a high-speed camera for photographing the ceramic turbine rotor, and when the temperature detected by the radiation thermometer exceeds an upper limit, the ceramic turbine rotor is photographed by the high-speed camera. And a trigger device. According to a third aspect of the present invention to achieve the above object, according to claim 1, further comprising a vibration sensor provided on a shaft portion of the ceramic turbine rotor for detecting vibration of the shaft portion, wherein the vibration sensor detects the vibration. and the upper limit value of the temperature that is, signals from the vibration sensor is equal to or to emergency stop the combustor when the condition of the upper limit value of the vibration increases occurring during breaking a fully together.

[0010]

In the hot spin test, the ceramic turbine rotor emits incandescent light due to the combustion gas from the combustor, and also emits light immediately before being destroyed by high stress. A radiation thermometer converts the amplitude of emitted light into an amount of energy, so it can capture the light emission phenomenon as a change in temperature. Accordingly, it is possible to clearly distinguish and detect whether the light emission phenomenon is immediately before the destruction.

[0011]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described in detail with reference to embodiments shown in the drawings. FIG. 1 shows a first embodiment of the present invention. As shown in the figure, in a test apparatus for performing a hot spin test of a ceramic turbine rotor,
The ceramic turbine rotor 1 is rotatably supported.
Alternatively, a power absorbing compressor impeller (not shown) is provided on the other end side.

A combustor 2 is provided upstream of the ceramic turbine rotor 1, and the combustion gas from the combustor 2 is blown onto the ceramic turbine rotor 1, whereby the ceramic turbine rotor 1 rotates at high speed. A fuel supply pipe 3 for supplying fuel is connected to the combustor 2.
The fuel supply pipe 3 is provided with a fuel cutoff valve 4.

Further, a tempered quartz glass window 5 is provided on the partition wall 6 facing the ceramic turbine rotor 1, and a pyrometer (trade name) 7 is provided as a radiation thermometer opposite to the tempered quartz glass window 5. . The radiation thermometer converts the amplitude amount of light emitted from the ceramic turbine rotor 1 into an energy amount and detects the energy amount as the temperature of the ceramic turbine rotor 1. The detected temperature measurement signal is output to the data processing device 9.

The pyrometer 7 of the present embodiment is connected to an infrared light in a wavelength band of 0.25 to 3 μm,
Light of about μm is captured at an ultra-high speed, and the amplitude of the light is converted into energy (current value) and detected as temperature. Therefore, the light emission phenomenon immediately before the ceramic is broken due to high stress can be reliably detected as a temperature change. On the other hand, a vibration sensor 8 for detecting vibration is provided on the shaft of the ceramic turbine rotor 1. Vibration sensor 8
Is output to the data processing device 9.

The data processing device 9 sets the primary stop condition when the temperature detected by the pyrometer 7 exceeds the upper limit, and sets the secondary stop condition when the speed of vibration rise caused by the vibration sensor 8 at the time of destruction exceeds the upper limit. Stop condition, primary,
When the secondary stop condition is satisfied, a combustion stop signal is output to the fuel cutoff valve 4, and the valve is closed to perform an emergency stop. The upper limit of the temperature for satisfying the primary condition may be, for example, a temperature about 50 to 100 ° C. higher than the steady state.

In the destruction detection device of this embodiment having the above-described configuration, the light emission phenomenon is detected as a temperature change by the pyrometer 7, so that even in the case of the ceramic turbine rotor 1 which emits incandescent light due to a high temperature in the hot spin test. The light emission phenomenon immediately before the destruction can be clearly grasped. That is, in the hot spin test, the ceramic turbine rotor 1 is blown with combustion gas,
Since it emits incandescent light, it is difficult to distinguish it from the light emission phenomenon immediately before its destruction.

However, in this embodiment, since the light amplitude is converted into energy by the pyrometer 7 and the light emission phenomenon is regarded as a temperature change, the incandescent light is simply emitted by the combustion gas from the combustor 2. Alternatively, it is possible to clearly distinguish whether the ceramic turbine rotor 1 has caused a light emission phenomenon immediately before it is broken. Further, the pyrometer 7 of the present embodiment has excellent responsiveness as compared with the case of detecting a light emission phenomenon itself that is visible light, such as a photodiode or a photomulti, so that it is possible to reliably perform destructive detection. It is safe because lubricating oil and the like do not ignite.

In the above embodiment, the pyrometer 7 and the vibration sensor 8 are used together, and when the primary and secondary stop conditions are satisfied, a combustion stop signal is sent from the data processor 9 to the fuel cutoff valve 4.
And the automatic emergency stop can be safely and reliably performed, which is advantageous. However, the vibration sensor 8 can be omitted if unnecessary.

FIG. 2 shows a second embodiment of the present invention. As shown in the drawing, in a test apparatus for performing a hot spin test of a ceramic turbine rotor, a ceramic turbine rotor 11 is rotatably supported, and a compressor impeller (not shown) is provided at the other end side and output is provided. Connected to the shaft. Ceramic turbine rotor 1
1 is provided with a combustor 12, and the combustion gas from the combustor 2 is blown to the ceramic turbine rotor 11, whereby the ceramic turbine rotor 11 rotates at high speed.

Further, two strengthened quartz glass windows 14 are provided on the partition wall 13 facing the ceramic turbine rotor 11, and a pyrometer (trade name) 15 as a radiation thermometer and a high speed A camera 16 is provided. The radiation thermometer converts the amplitude of light emitted from the ceramic turbine rotor 11 into an energy, and detects the energy as the temperature of the ceramic turbine rotor 11. The detected temperature measurement signal is output to the trigger device 17.

The pyrometer 15 of this embodiment has a
Infrared light in a wavelength band of ３3 μm, particularly light of about 1 μm, is captured at a very high speed via an optical fiber, and the amplitude of the light is converted into energy (current value) and detected as temperature. For this reason, a phenomenon in which the ceramic emits light immediately before breaking due to high stress can be reliably detected as a temperature change.

As the high-speed camera 16, for example, a camera capable of photographing tens of thousands of frames per second can be used. The trigger device 17 triggers when the temperature detected by the pyrometer 7 exceeds the upper limit, outputs a photographing command signal to the high-sensitivity camera 16, and causes the ceramic turbine rotor 11 to photograph. As its upper limit,
For example, the temperature may be about 50 to 100 ° C. higher than the steady state.

In the destruction detection device of this embodiment having the above-described configuration, the light emission phenomenon is detected as a temperature change by the pyrometer 15, so that even in the case of the ceramic turbine rotor 11 which emits incandescent light due to high temperature in the hot spin test. The light emission phenomenon immediately before the destruction can be clearly grasped, so that the mechanism of the destruction of the ceramic turbine rotor 11 in the high-temperature gas can be reliably photographed.

The above embodiment is an example in which the present invention is applied to a hot spin test. However, the present invention is not limited to this, but includes a cold spin test, a high temperature turbine test, a bench test equivalent to an actual engine, and a turbocharger. It can be widely used for rotor spin tests and the like.

[0025]

As described above in detail with reference to the embodiments, in the present invention, in the hot spin test, the light emission phenomenon immediately before the destruction of the ceramic is not detected as a light emission phenomenon, but the light emission phenomenon is changed with temperature. As a result, destruction can be detected with good responsiveness.

[Brief description of the drawings]

FIG. 1 is a configuration diagram of a destruction detection device according to a first embodiment of the present invention.

FIG. 2 is a configuration diagram of a destruction detection device according to a second embodiment of the present invention.

[Explanation of symbols]

 Reference Signs List 1,11 ceramic turbine rotor 2,12 combustor 3 fuel supply pipe 4 fuel cutoff valve 5,14 tempered quartz glass window 6,13 partition wall 7,15 pyrometer 8 vibration sensor 9 data processing device 16 high-sensitivity camera 17 trigger device

──────────────────────────────────────────────────続 き Continuation of the front page (58) Field surveyed (Int. Cl. ⁷ , DB name) G01M 19/00 G01J 5/00-5/62 JICST file (JOIS)

Claims (3)

(57) [Claims] 1. A radiation thermometer for converting an amplitude amount of light emitted from a ceramic turbine rotor immediately before destruction in a specific wavelength range into an energy amount and detecting the energy amount at a very high speed as the temperature of the ceramic turbine rotor; A ceramic comprising: a combustor for blowing combustion gas to a turbine rotor; and a data processing device for emergency-stopping the combustor on condition that a temperature detected by the radiation thermometer exceeds an upper limit value. Turbine rotor breakdown detector. 2. A radiation thermometer for converting an amplitude in a specific wavelength range of light emitted from a ceramic turbine rotor immediately before destruction into an energy, and detecting the energy as a temperature of the ceramic turbine rotor at a very high speed; A high-speed camera for photographing the turbine rotor, and a trigger device for photographing the ceramic turbine rotor by the high-speed camera when the temperature detected by the radiation thermometer exceeds an upper limit. Detection device for ceramic turbine rotor. 3. The apparatus according to claim 1, further comprising a vibration sensor provided on a shaft of the ceramic turbine rotor for detecting vibration of the shaft, wherein an upper limit value of a temperature detected by the radiation thermometer; breakdown detecting apparatus of the ceramic turbine rotor signal is characterized by causing an emergency stop of the combustor when the condition of the upper limit value of the vibration increases occurring during fracture equipped both from the vibration sensor.