A rocket engine turbine speed measurement device and method

Abstract

The application provides a rocket engine turbine rotating speed measuring device and method. The rocket engine turbine rotating speed measuring device comprises a photoelectric detector, a turbine blade is rotatably installed in a turbine pump shell, a through hole is arranged on the turbine pump shell, the photoelectric detector is located on the outside of the turbine pump shell, and the position of the photoelectric detector is adjacent to the position of the through hole.

Description

Technical Field

[0001] This invention relates to the field of rocket engine turbine monitoring equipment technology, and in particular to a rocket engine turbine speed measuring device and method. Background Technology

[0002] Existing methods for measuring the rotational speed of rocket engine turbopumps mostly rely on magnetic media measurement. This involves mounting a magnetic object on the turbine shaft and measuring the change in the magnetic field generated by the rotation of the turbine blades. This method typically requires drilling holes in the turbine shaft to embed the magnetic object (which compromises the structural integrity of the turbine shaft and affects its strength). The holes then need to be welded and sealed. To ensure that the magnetic object is not demagnetized by high temperatures, the manufacturing process is extremely cumbersome and complex.

[0003] In existing measurement methods, a hole needs to be drilled in the turbine shaft, and a magnet needs to be placed inside the hole. The hole is then welded shut to prevent the magnet from falling off. When the turbine rotates, the magnet rotates with it, generating an alternating magnetic field at the speed sensor location. Speed ​​sensors are mostly coil structures; when the alternating magnetic field passes through the coil, it generates electromagnetic induction, producing a voltage that is then measured and sensed by the downstream device.

[0004] The specific drawbacks of the existing solution are as follows: 1. The rotational speed is measured using a magnetic medium, which is easily affected by magnetic field interference in the environment. When magnetic field interference exists in the environment, it will cause the measurement results to be distorted.

[0005] 2. The structure is complex, requiring the placement of magnetic materials on the turbine shaft, which increases the complexity of the structure. In addition, placing magnetic materials in the turbine shaft may affect the dynamic balance of the turbine during rotation and reduce the structural strength.

[0006] 3. Welding is required for fixation. To ensure that the magnetic body will not be demagnetized at high temperatures, the welding requirements are high. In addition, the risk of demagnetization at high temperatures must also be considered during use. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to provide a rocket engine turbine speed measuring device and method to address the shortcomings of the prior art.

[0008] The technical solution of the present invention to solve the above-mentioned technical problems is as follows: A rocket engine turbine speed measuring device includes: a photodetector, a turbine blade rotatably mounted in a turbine pump housing, a through hole provided on the turbine pump housing, and the photodetector located on the outside of the turbine pump housing, with the position of the photodetector adjacent to the position of the through hole.

[0009] The beneficial effects of adopting the technical solution of this invention are as follows: when the fan blade sweeps across the small hole, the flame cannot be transmitted; when the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by an externally placed photoelectric detector, thus achieving the measurement of turbine speed. Light is used as the measurement medium to achieve the measurement of turbine pump speed. It has strong anti-interference ability; light as a medium has a strong ability to resist electrical and magnetic signal interference. No additional devices are required, and the turbine shaft is not damaged, effectively reducing structural complexity and manufacturing difficulty. No magnetic material needs to be placed on the pump shaft, thus not damaging the physical structure of the pump shaft. Optical measurement provides strong anti-interference ability.

[0010] Furthermore, a transparent sealing component is installed at the through hole.

[0011] The beneficial effect of adopting the above-mentioned further technical solution is that by using a transparent sealing component to seal the small hole, the flame of combustion inside the turbine can be transmitted through the small hole without causing gas leakage.

[0012] Furthermore, the transparent sealing component is made of sapphire glass.

[0013] The beneficial effect of adopting the above-mentioned further technical solution is that by using transparent materials such as glass to seal the small hole, the flame from combustion inside the turbine can be transmitted through the small hole without causing gas leakage. Sapphire glass is used to seal the hole to avoid compromising the sealing performance of the turbine pump housing.

[0014] Furthermore, the photodetector is a photodiode, a phototransistor, an avalanche diode, a photomultiplier tube, or a single-photon counter.

[0015] The beneficial effect of adopting the above-mentioned further technical solutions is that photodetectors, including but not limited to photodiodes, phototransistors, avalanche diodes, photomultiplier tubes, single-photon counters, and other devices capable of converting optical signals into electrical signals, facilitate the selection of photodetector types according to actual needs, thus improving applicability.

[0016] Furthermore, the photodetector is electrically connected to an IV conversion circuit, the IV conversion circuit is electrically connected to a signal amplification circuit, the signal amplification circuit is electrically connected to a data acquisition circuit, and the data acquisition circuit is electrically connected to a signal processing circuit.

[0017] The beneficial effect of adopting the above-mentioned further technical solution is that when the turbine rotates, the fan blades will continuously brush past the small hole, causing the light emitted from the small hole to show changes in brightness. By placing a photodetector at the position of the small hole, the change in light intensity can be identified, and the light signal can be converted into an electrical signal. Then, through the IV conversion circuit and signal amplification circuit, the signal is amplified to a reasonable range. Finally, through the data acquisition circuit and signal processing circuit, the analog signal is converted into a digital signal, and the data is processed to obtain the final rotational speed.

[0018] Furthermore, the through hole is located near the turbine blade; when the rocket engine is operating, the turbine blade periodically blocks the through hole.

[0019] The beneficial effect of adopting the above-mentioned further technical solution is that when the fan blade sweeps into the small hole, the flame cannot be transmitted. When the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by the photoelectric detector placed outside, thereby realizing the measurement of the turbine speed.

[0020] Furthermore, when the rocket engine is operating, there is a burning flame inside the turbopump housing.

[0021] The beneficial effect of adopting the above-mentioned further technical solution is that when the fan blade sweeps across the small hole, the flame cannot be transmitted; when the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by an externally placed photoelectric detector, thus achieving the measurement of turbine speed. Light is used as the measurement medium to achieve the measurement of turbine pump speed. It has strong anti-interference ability; light as a medium has a strong ability to resist electrical and magnetic signal interference.

[0022] In addition, the present invention also provides a method for measuring the turbine speed of a rocket engine. Based on the above-mentioned rocket engine turbine speed measuring device, the method for measuring the turbine speed of a rocket engine includes: S1, when the rocket engine is working, collecting the change in light intensity of the flame burning inside the turbine pump casing through a photoelectric detector; S2, obtaining the turbine speed of the rocket engine based on the change in light intensity of the flame burning inside the turbine pump casing.

[0023] The beneficial effects of adopting the technical solution of this invention are as follows: when the fan blade sweeps across the small hole, the flame cannot be transmitted; when the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by an externally placed photoelectric detector, thus achieving the measurement of turbine speed. Light is used as the measurement medium to achieve the measurement of turbine pump speed. It has strong anti-interference ability; light as a medium has a strong ability to resist electrical and magnetic signal interference. No additional devices are required, and the turbine shaft is not damaged, effectively reducing structural complexity and manufacturing difficulty. No magnetic material needs to be placed on the pump shaft, thus not damaging the physical structure of the pump shaft. Optical measurement provides strong anti-interference ability.

[0024] Further, step S1 includes: S11, when the rocket engine is working, the flame of combustion inside the rocket engine turbine is transmitted through the through hole; wherein, when the turbine blade sweeps into the through hole, the flame cannot be transmitted, and when the turbine blade leaves the through hole, the flame is transmitted to the outside through the through hole; S12, the change in the light intensity of the flame of combustion inside the turbine pump casing is collected by an externally installed photoelectric detector.

[0025] The beneficial effect of adopting the above-mentioned further technical solution is that when the turbine rotates, the fan blades continuously brush past the small hole, causing the light emitted from the hole to exhibit changes in brightness. By placing a photodetector at the hole location, the changes in light intensity can be identified, and the light signal can be converted into an electrical signal. Light is used as the measurement medium to achieve the measurement of the turbine pump speed. It has strong anti-interference capabilities; light as a medium has a strong ability to resist electrical and magnetic signal interference.

[0026] Further, step S2 includes: S21, converting the optical signal into an electrical signal using a photodetector; S22, amplifying the electrical signal using an IV conversion circuit and a signal amplification circuit to form an analog signal; S23, converting the analog signal into a digital signal using a data acquisition circuit and a signal processing circuit, and processing the data to obtain the turbine speed of the rocket engine.

[0027] The beneficial effect of adopting the above-mentioned further technical solution is that when the turbine rotates, the fan blades will continuously brush past the small hole, causing the light emitted from the small hole to show changes in brightness. By placing a photodetector at the position of the small hole, the change in light intensity can be identified, and the light signal can be converted into an electrical signal. Then, through the IV conversion circuit and signal amplification circuit, the signal is amplified to a reasonable range. Finally, through the data acquisition circuit and signal processing circuit, the analog signal is converted into a digital signal, and the data is processed to obtain the final rotational speed.

[0028] The advantages of additional aspects of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 This is one of the structural schematic diagrams of the rocket engine turbine speed measuring device provided in an embodiment of the present invention.

[0031] Figure 2 This is a second schematic diagram of the structure of the rocket engine turbine speed measuring device provided in an embodiment of the present invention.

[0032] Figure 3 This is the third schematic diagram of the structure of the rocket engine turbine speed measuring device provided in the embodiment of the present invention.

[0033] Figure 4 This is one of the schematic flowcharts of a rocket engine turbine speed measurement method provided in an embodiment of the present invention.

[0034] Figure 5 This is the second schematic flowchart of a rocket engine turbine speed measurement method provided in an embodiment of the present invention.

[0035] The following are the symbols and their meanings: 1. Photodetector; 2. Turbine pump housing; 3. Turbine blade; 4. Through hole; 5. IV conversion circuit; 6. Signal amplification circuit; 7. Data acquisition circuit; 8. Signal processing circuit. Detailed Implementation

[0036] The principles and features of the present invention are described below with reference to the accompanying drawings. The embodiments described are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0038] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0039] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0040] In the description of the embodiments of the present invention, it should be noted that if terms such as "upper", "lower", "horizontal", "inner" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the invention is usually placed during use, they are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0041] In the description of the embodiments of the present invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0042] like Figures 1 to 3 As shown, an embodiment of the present invention provides a rocket engine turbine speed measuring device, including: a photodetector 1, a turbine blade 3 rotatably mounted in a turbine pump housing 2, a through hole 4 provided on the turbine pump housing 2, the photodetector 1 being located on the outside of the turbine pump housing 2, and the position of the photodetector 1 being adjacent to the position of the through hole 4.

[0043] The beneficial effects of adopting the technical solution of this invention are as follows: when the fan blade sweeps across the small hole, the flame cannot be transmitted; when the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by an externally placed photoelectric detector, thus achieving the measurement of turbine speed. Light is used as the measurement medium to achieve the measurement of turbine pump speed. It has strong anti-interference ability; light as a medium has a strong ability to resist electrical and magnetic signal interference. No additional devices are required, and the turbine shaft is not damaged, effectively reducing structural complexity and manufacturing difficulty. No magnetic material needs to be placed on the pump shaft, thus not damaging the physical structure of the pump shaft. Optical measurement provides strong anti-interference ability.

[0044] Figure 1 The diagram shows a light passing through the through-hole when the turbine blades do not block it. Figure 2 This diagram illustrates that when the turbine blades block the through-hole, no light passes through it.

[0045] This invention provides a rocket engine turbine speed measuring device, which can be a photoelectric measuring device. A small hole (through hole) is opened in the turbine pump housing (turbine pump casing), and the hole (through hole) is sealed with a transparent material such as glass, allowing the flame from combustion inside the turbine to escape through the hole (through hole) without causing gas leakage. When the turbine blade sweeps across the hole (through hole), the flame cannot escape; when the blade leaves the hole, the flame escapes to the outside. The intensity change of the light (flame) can be sensed by an externally placed photoelectric detector, thus measuring the turbine speed. Figure 1 and Figure 2 The turbine blades, pump housing, orifice, and photodiode are for illustrative purposes only. The actual size of the orifice and photodiode is much smaller than that of the turbine pump housing and turbine blades.

[0046] Photodetector: A device that converts light signals into electrical signals. Generally, different light intensities correspond to different electrical signal intensities (such as current and voltage). There are also devices that convert different wavelengths and intensities of light into electrical signals separately. These devices are more complex.

[0047] Photoelectric detection technology is widely used in various fields, such as fiber optic communication, optical ranging, and electronic cameras. By converting light into electricity, it analyzes the information carried in the light, such as wavelength and intensity, to achieve various communication and measurement purposes. This invention applies this technology to the field of turbopump speed measurement, innovatively using light as the measurement medium to measure the speed of turbopumps.

[0048] Furthermore, a transparent sealing component is installed at the through hole 4.

[0049] The beneficial effect of adopting the above-mentioned further technical solution is that by using a transparent sealing component to seal the small hole, the flame of combustion inside the turbine can be transmitted through the small hole without causing gas leakage.

[0050] Furthermore, the transparent sealing component is made of sapphire glass.

[0051] The beneficial effect of adopting the above-mentioned further technical solution is that by using transparent materials such as glass to seal the small hole, the flame from combustion inside the turbine can be transmitted through the small hole without causing gas leakage. Sapphire glass is used to seal the hole to avoid compromising the sealing performance of the turbine pump housing.

[0052] Among them, sapphire glass encapsulates, but is not limited to, light-transmitting materials that can seal openings (through holes).

[0053] Furthermore, the photodetector 1 is a photodiode, a phototransistor, an avalanche diode, a photomultiplier tube, or a single-photon counter.

[0054] The beneficial effect of adopting the above-mentioned further technical solutions is that photodetectors, including but not limited to photodiodes, phototransistors, avalanche diodes, photomultiplier tubes, single-photon counters, and other devices capable of converting optical signals into electrical signals, facilitate the selection of photodetector types according to actual needs, thus improving applicability.

[0055] like Figure 3 As shown, the photodetector 1 is further electrically connected to an IV conversion circuit 5, the IV conversion circuit 5 is electrically connected to a signal amplification circuit 6, the signal amplification circuit 6 is electrically connected to a data acquisition circuit 7, and the data acquisition circuit 7 is electrically connected to a signal processing circuit 8.

[0056] The beneficial effect of adopting the above-mentioned further technical solution is that when the turbine rotates, the fan blades will continuously brush past the small hole, causing the light emitted from the small hole to show changes in brightness. By placing a photodetector at the position of the small hole, the change in light intensity can be identified, and the light signal can be converted into an electrical signal. Then, through the IV conversion circuit and signal amplification circuit, the signal is amplified to a reasonable range. Finally, through the data acquisition circuit and signal processing circuit, the analog signal is converted into a digital signal, and the data is processed to obtain the final rotational speed.

[0057] like Figures 1 to 3 As shown, the position of the through hole 4 is adjacent to the position of the turbine blade 3; when the rocket engine is working, the turbine blade 3 periodically blocks the through hole 4.

[0058] The beneficial effect of adopting the above-mentioned further technical solution is that when the fan blade sweeps into the small hole, the flame cannot be transmitted. When the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by the photoelectric detector placed outside, thereby realizing the measurement of the turbine speed.

[0059] Furthermore, when the rocket engine is operating, there is a burning flame inside the turbopump housing 2.

[0060] The beneficial effect of adopting the above-mentioned further technical solution is that when the fan blade sweeps across the small hole, the flame cannot be transmitted; when the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by an externally placed photoelectric detector, thus achieving the measurement of turbine speed. Light is used as the measurement medium to achieve the measurement of turbine pump speed. It has strong anti-interference ability; light as a medium has a strong ability to resist electrical and magnetic signal interference.

[0061] The present invention provides a rocket engine turbine speed measuring device, which can be a photoelectric rocket engine turbine speed measuring device. A through hole is drilled in the turbine pump housing (turbopump shell) to transmit the flame generated during combustion inside the turbine pump to the outside. Then, sapphire glass is used to seal the hole (through hole) to avoid damaging the sealing of the turbine pump housing.

[0062] When the turbine rotates, the fan blades (turbine blades) continuously brush past the small hole (through hole), causing the light emitted from the hole (through hole) to change in brightness. By placing a photodetector at the position of the small hole (through hole), the change in light intensity can be detected, and the light signal can be converted into an electrical signal. Then, through an IV conversion circuit and a signal amplification circuit, the signal is amplified to a reasonable range. Finally, through a data acquisition circuit and a signal processing circuit, the analog signal is converted into a digital signal, and the data is processed to obtain the final rotational speed.

[0063] It has strong anti-interference ability; light, as a medium, has a strong ability to resist electrical and magnetic signal interference.

[0064] No additional devices are needed, and the turbine rod will not be damaged, effectively reducing structural complexity and processing difficulty.

[0065] There is no need to place a magnetic object on the pump shaft, and the physical structure of the pump shaft is not damaged.

[0066] Optical measurement with strong anti-interference ability.

[0067] like Figure 4 As shown, in addition, the present invention also provides a method for measuring the turbine speed of a rocket engine. Based on the above-mentioned rocket engine turbine speed measuring device, the method for measuring the turbine speed of a rocket engine includes: S1, when the rocket engine is working, collecting the change in the light intensity of the flame burning inside the turbine pump casing through a photoelectric detector; S2, obtaining the turbine speed of the rocket engine based on the change in the light intensity of the flame burning inside the turbine pump casing.

[0068] The beneficial effects of adopting the technical solution of this invention are as follows: when the fan blade sweeps across the small hole, the flame cannot be transmitted; when the fan blade leaves the small hole, the flame is transmitted from the small hole to the outside. The change in light intensity can be sensed by an externally placed photoelectric detector, thus achieving the measurement of turbine speed. Light is used as the measurement medium to achieve the measurement of turbine pump speed. It has strong anti-interference ability; light as a medium has a strong ability to resist electrical and magnetic signal interference. No additional devices are required, and the turbine shaft is not damaged, effectively reducing structural complexity and manufacturing difficulty. No magnetic material needs to be placed on the pump shaft, thus not damaging the physical structure of the pump shaft. Optical measurement provides strong anti-interference ability.

[0069] Further, step S1 includes: S11, when the rocket engine is working, the flame of combustion inside the rocket engine turbine is transmitted through the through hole; wherein, when the turbine blade sweeps into the through hole, the flame cannot be transmitted, and when the turbine blade leaves the through hole, the flame is transmitted to the outside through the through hole; S12, the change in the light intensity of the flame of combustion inside the turbine pump casing is collected by an externally installed photoelectric detector.

[0070] The beneficial effect of adopting the above-mentioned further technical solution is that when the turbine rotates, the fan blades continuously brush past the small hole, causing the light emitted from the hole to exhibit changes in brightness. By placing a photodetector at the hole location, the changes in light intensity can be identified, and the light signal can be converted into an electrical signal. Light is used as the measurement medium to achieve the measurement of the turbine pump speed. It has strong anti-interference capabilities; light as a medium has a strong ability to resist electrical and magnetic signal interference.

[0071] Further, step S2 includes: S21, converting the optical signal into an electrical signal using a photodetector; S22, amplifying the electrical signal using an IV conversion circuit and a signal amplification circuit to form an analog signal; S23, converting the analog signal into a digital signal using a data acquisition circuit and a signal processing circuit, and processing the data to obtain the turbine speed of the rocket engine.

[0072] The beneficial effect of adopting the above-mentioned further technical solution is that when the turbine rotates, the fan blades will continuously brush past the small hole, causing the light emitted from the small hole to show changes in brightness. By placing a photodetector at the position of the small hole, the change in light intensity can be identified, and the light signal can be converted into an electrical signal. Then, through the IV conversion circuit and signal amplification circuit, the signal is amplified to a reasonable range. Finally, through the data acquisition circuit and signal processing circuit, the analog signal is converted into a digital signal, and the data is processed to obtain the final rotational speed.

[0073] like Figure 5 As shown, the rocket engine turbine speed measurement method provided in this embodiment of the invention includes: start-up, turbine start-up, photoelectric conversion, IV conversion, signal amplification, data acquisition, signal processing, and output speed.

[0074] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A rocket engine turbine speed measuring device, characterized by, include: A photodetector is provided. Turbine blades are rotatably mounted in a turbine pump housing. The turbine pump housing has a through hole. The photodetector is located on the outside of the turbine pump housing, and its position is adjacent to the position of the through hole.

2. A rocket engine turbine speed measuring device as in claim 1, wherein A transparent sealing component is installed at the through hole.

3. A rocket engine turbine speed measuring device as recited in claim 2, wherein, The transparent sealing component is made of sapphire glass.

4. A rocket engine turbine speed measuring device as in claim 1, wherein The photodetector is a photodiode, phototransistor, avalanche diode, photomultiplier tube, or single-photon counter.

5. A rocket engine turbine speed measuring device as in claim 1, wherein, The photodetector is electrically connected to an IV conversion circuit, the IV conversion circuit is electrically connected to a signal amplification circuit, the signal amplification circuit is electrically connected to a data acquisition circuit, and the data acquisition circuit is electrically connected to a signal processing circuit.

6. A rocket engine turbine speed measuring device as in claim 1, wherein, The through hole is located near the turbine blade; when the rocket engine is operating, the turbine blade periodically blocks the through hole.

7. A rocket engine turbine speed measuring device as in claim 1, wherein, When the rocket engine is working, there is a burning flame inside the turbopump housing.

8. A method of measuring the rotational speed of a rocket engine turbine, characterized in that, A rocket engine turbine speed measuring device according to any one of claims 1 to 7, the rocket engine turbine speed measuring method includes: S1, when the rocket engine is working, collecting the change in light intensity of the flame inside the turbine pump casing through a photoelectric detector; S2. The turbine speed of the rocket engine is obtained based on the change in the intensity of the flame from the combustion inside the turbine pump casing.

9. A method of measuring the speed of rotation of a rocket engine turbine as defined in claim 8, wherein Step S1 includes: S11, when the rocket engine is working, the flame of combustion inside the rocket engine turbine is transmitted through the through hole; wherein, when the turbine blade sweeps into the through hole, the flame cannot be transmitted, and when the turbine blade leaves the through hole, the flame is transmitted to the outside through the through hole. S12. The intensity of the flame inside the turbine pump casing is collected by an externally installed photoelectric detector.

10. A method of measuring the speed of rotation of a rocket engine turbine as defined in claim 8, wherein Step S2 includes: S21, converting the optical signal into an electrical signal using a photodetector; S22. The electrical signal is amplified by the IV conversion circuit and the signal amplification circuit to form an analog signal; S23. The analog signal is converted into a digital signal through the data acquisition circuit and the signal processing circuit, and the data is processed to obtain the turbine speed of the rocket engine.

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