Compressor radial clearance measuring device and method

Abstract

The gas compressor radial clearance measuring device comprises an optical fiber probe and a height fluctuation structure arranged on the surface of a rotor part, the optical fiber probe is arranged in a stator part, faces the rotor part and is used for detecting the distance between the optical fiber probe and the rotor part, and the height fluctuation structure is arranged to be higher than or lower than the surface of the rotor part. By acquiring test data of the optical fiber probe relative to the surface and the height fluctuation structure of the rotor piece in real time, the labyrinth gap change can be quickly and accurately determined. The invention further provides a gas compressor radial clearance measuring method.

Description

Technical Field

[0001] The invention relates to the field of aeroengine testing, and in particular to the field of compressor radial clearance testing. Background Art

[0002] The test verification of aircraft engine compressor is an essential step in the design process of aircraft engines. In the process of compressor performance test, the design, detection and control of the grate clearance are crucial. The radial clearance between the grate tooth tip of the aircraft engine compressor rotor and the stator honeycomb has a great influence on the aerodynamic performance parameters of the compressor, such as efficiency and margin, and thus has a great impact on the safety and economy of the compressor.

[0003] In the prior art, the measurement of the clearance of the compressor comb teeth generally adopts the method of "disassembly after removal - detection of the scraping condition of the stator honeycomb - reinstallation", which is time-consuming and inefficient. At present, it is difficult to evaluate the measurement accuracy of the clearance sensor and to confirm the accuracy of the measured clearance.

[0004] In view of this, it is necessary to propose a compressor radial clearance measurement method to solve the above problems. Summary of the invention

[0005] An object of the present invention is to provide a compressor radial clearance measuring device which can measure the compressor radial clearance simply and accurately.

[0006] To achieve the above-mentioned purpose, a compressor radial clearance measuring device includes a fiber optic probe and a height fluctuation structure arranged on the surface of the rotor component. The fiber optic probe is arranged in the stator component and faces the direction of the rotor component, and is used to detect the distance between the fiber optic probe and the rotor component. The height fluctuation structure is arranged to be higher or lower than the surface of the rotor component.

[0007] In one or more embodiments, the stator component includes a sealed honeycomb structure, and the optical fiber probe is arranged in the sealed honeycomb structure.

[0008] In one or more embodiments, the rotor member includes a drum and a comb structure, and the height fluctuation structure is a raised block, and the raised block is arranged on the outer surface of the drum.

[0009] In one or more embodiments, the axial position of the optical fiber probe is set at the sealed honeycomb structure corresponding to the gap between adjacent comb teeth of the comb tooth structure, and the radial direction of the optical fiber probe is the engine axis direction.

[0010] In one or more embodiments, the height fluctuation structure is a groove.

[0011] In one or more embodiments, the compressor clearance measurement device further includes a control module connected to the optical fiber probe in real-time signal communication.

[0012] In one or more embodiments, a plurality of height fluctuation structures are arranged on the surface of the rotor member.

[0013] Another object of the present invention is to provide a method for measuring the radial clearance of a compressor. Using the above-mentioned compressor clearance measuring device, the method includes the following steps: setting a fiber optic probe in the stator of the compressor so that the fiber optic probe is facing the direction of the rotor; running the compressor, using the fiber optic probe to collect multiple sets of clearance data from the surface of the rotor part to the stator, and obtaining the rotation parameters of the rotor part through the clearance data.

[0014] In one or more embodiments, it is determined whether the plurality of sets of clearance data are within an allowable clearance range to determine whether the rotor component is eccentric.

[0015] The above-mentioned compressor radial clearance measurement device and method are configured by setting a fiber optic probe located in the stator component and a height fluctuation structure arranged on the rotor component. The height fluctuation structure and the area of ​​the non-height fluctuation structure on the rotor component make the data read by the fiber optic probe significantly different. Through the real-time collected data, the comb tooth clearance change can be quickly and accurately determined, and then the corresponding relationship between the speed and the clearance change can be analyzed. The position of the fiber optic probe can be adjusted according to the actual situation, and the installation flexibility is high. In conjunction with the height fluctuation structure, it can realize the monitoring of various data such as speed, rotor vibration, eccentricity, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0017] Figure 1 is a schematic diagram of the installation position of the optical fiber probe and the protrusion block;

[0018] Figure 2 yes Figure 1 Cross-section view in the AA direction;

[0019] Figure 3 Schematic diagram of the location of the groove;

[0020] Figure 4 yes Figure 2 Cross-sectional view along the BB direction.

[0021] Description of Reference Numerals

[0022] 1. Sealed honeycomb structure

[0023] 2 Comb tooth structure

[0024] 3 Fiber Optic Probe

[0025] 4 Raised blocks

[0026] 5 Drum

[0027] 6 Grooves DETAILED DESCRIPTION

[0028] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0029] It should be noted that these and other subsequent drawings are only examples and are not drawn to scale, and should not be used to limit the actual scope of protection required by the present invention.

[0030] The radial clearance between the tip of the rotor grate teeth and the stator honeycomb of an aircraft engine compressor has a significant impact on the aerodynamic performance parameters of the compressor. In the prior art, the measurement of the grate clearance of the compressor generally adopts the method of "disassembly after disassembly - inspection of the scraping condition of the stator honeycomb - re-installation", which is time-consuming and inefficient. In addition, the measurement accuracy of the clearance sensor is difficult to evaluate, and it is difficult to confirm the accuracy of the measured clearance.

[0031] The compressor of the aircraft engine includes a rotor part and a stator part, the rotor part includes a drum 5 and a comb tooth structure 2, and the stator part includes a sealing honeycomb structure 1. Based on this, the compressor radial clearance measuring device disclosed in the present invention includes a fiber optic probe 3 and a height fluctuation structure, and the fiber optic probe 3 is arranged in the stator part and faces the direction of the rotor part, and is used to detect the distance between the fiber optic probe and the surface of the rotor part.

[0032] The height fluctuation structure is arranged to be higher or lower than the surface of the rotor member, so as to make the gap data when the optical fiber probe detects the height fluctuation structure and the non-height fluctuation structure area on the rotor member have significant differences.

[0033] like Figure 1 and Figure 2 As shown, the height fluctuation structure is a raised block, and the rotor member includes a drum and a comb structure. The raised block 4 is arranged on the outer surface of the drum 5, which is higher than the non-raised block area by a height X. Then, during one rotation of the rotor member, the optical fiber probe 3 reads the gap data at the raised block which is always less than X than that on other surfaces of the rotor member.

[0034] Therefore, by extracting and identifying the change rules of the collected data, the rotor rotation period can be obtained, and the real-time speed can be converted. The radial height of the raised block is known, for example, 1mm. During the experiment, when the optical fiber probe sweeps over the raised block, the collected gap data will change instantaneously, such as about 1mm, which corresponds to the radial height of the raised block. According to the change of the gap data, it can be known that the optical fiber probe sweeps over the raised block once every several seconds, and the rotor rotation period is obtained, which can be converted into the real-time speed. After obtaining the real-time speed at each stage of the test, the corresponding relationship between the speed and the gap change can be analyzed.

[0035] In addition, if the designed boss height is 1mm, the actual distance between the boss top and the honeycomb can be obtained through the fiber optic probe. By comparing the data measured by the gap sensor, the accuracy of the gap sensor can be evaluated, thereby correcting the actual measured value of the comb tooth gap.

[0036] When the sampling frequency is high enough, in some embodiments, the optical fiber probe is also used to detect vibration parameters of the rotor component. For example, the optical fiber probe detects the vibration of the rotor drum, including amplitude and frequency, and establishes the relationship between the drum vibration and the rotation speed. Usually, the sampling frequency is greater than 50,000 Hz.

[0037] In some embodiments, multiple height fluctuation structures can also be set on the surface of the rotor component. For example, when no less than three protrusions 4 are set circumferentially of the drum, the real-time concentricity, eccentricity and eccentricity angle of the rotor drum relative to the stator can be monitored by analyzing the radial spacing between the protrusions 4 and the sealing honeycomb structure 1.

[0038] It is understandable that, based on the same principle, in order to achieve the above beneficial effects, the highly fluctuating structure is Figure 3 and Figure 4 The groove 6 shown. The groove 6 is 1mm lower than the outer surface of the drum. When the optical fiber probe 3 rotates one circle of the rotor, the gap data read at the groove 6 is always 1mm more than that of other surfaces of the rotor. By real-time data collection, the period, time, frequency and size of the data read by the optical fiber probe are determined, whether the rotor is eccentric and the amount of eccentricity are determined, and test data such as the actual rotor period are obtained to correct the calibrated rotation parameters of the rotor.

[0039] In some embodiments, the device further comprises a control module, which is connected to the optical fiber probe in real time signal, and is used to receive the gap data measured by the optical fiber probe 3 in real time, and perform data analysis.

[0040] The optical fiber probe can refer to the optical fiber probe structure described in Chinese patent publication CN113310421.

[0041] As in Figure 1 and Figure 2In the illustrated embodiment, the optical fiber probe is inserted into a sealed honeycomb structure serving as a stator. Preferably, the axial position of the optical fiber probe is set at the sealed honeycomb structure corresponding to the gap between adjacent comb teeth of the comb tooth structure, and the radial direction of the optical fiber probe is the engine axis direction.

[0042] After the compressor starts running, the drum, which is the rotor component, rotates clockwise. As the temperature rises, the drum gradually expands. The fiber optic probe transmits the collected data to the data analysis equipment in real time. The real-time collected data can quickly and accurately determine the change in the comb tooth gap.

[0043] The above device has a simple structure and can realize real-time acquisition of the comb tooth gap. The position of the optical fiber probe can be adjusted according to the actual situation, and the installation flexibility is high. The test block can realize the monitoring of various data such as speed, rotor vibration, eccentricity, etc. The aircraft engine compressor with this structure is helpful to evaluate the changing trend of the comb tooth gap and guide the subsequent optimization design.

[0044] In combination with the introduction to the above-mentioned compressor radial clearance measuring device, a compressor radial clearance measuring method can also be understood, which includes the following steps: setting the fiber optic probe in the stator of the compressor so that the fiber optic probe is facing the direction of the rotor; running the compressor, using the fiber optic probe to collect multiple sets of clearance data from the surface of the rotor part to the stator, and obtaining the rotation parameters of the rotor part through the clearance data.

[0045] The rotation parameters include rotor eccentricity, rotor eccentricity angle, rotor amplitude and frequency, and other parameters related to rotor rotation.

[0046] Specifically, it is possible to determine whether the rotor is eccentric and the amount of eccentricity by determining whether multiple sets of clearance data are within the clearance allowable range; or to calculate the rotor period by using multiple sets of clearance data.

[0047] The above method avoids the process of "disassembly - detection of stator honeycomb scraping - re-installation", solves the problem of long time consumption and low efficiency of the existing technology, has a simple structure, and by setting a height fluctuation structure on the surface of the rotor part, it can quickly and accurately determine the change of the comb tooth gap. The detection values ​​at the non-height fluctuation structure on the combined rotor part can realize the calculation of various data such as rotation speed, rotor vibration, eccentricity, etc.

[0048] The present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or multiple times in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0049] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A compressor radial clearance measuring device, wherein the compressor comprises a rotor component and a stator component, and is characterized in that: The measuring device comprises: an optical fiber probe, disposed in the stator component and facing the rotor component, and used for detecting the distance between the optical fiber probe and the rotor component; and The height fluctuation structure is arranged on the surface of the rotor component and is arranged to be higher or lower than the surface of the rotor component.

2. The compressor radial clearance measuring device according to claim 1, characterized in that: The stator component comprises a sealed honeycomb structure, and the optical fiber probe is arranged in the sealed honeycomb structure.

3. The compressor radial clearance measuring device according to claim 2, characterized in that: The rotor component comprises a drum and a comb tooth structure, the height fluctuation structure is a protrusion block, and the protrusion block is arranged on the outer surface of the drum.

4. The compressor radial clearance measuring device according to claim 3, characterized in that: The axial position of the optical fiber probe is set at the sealed honeycomb structure corresponding to the gap between adjacent comb teeth of the comb tooth structure, and the radial direction of the optical fiber probe is the engine axis direction.

5. The compressor radial clearance measuring device according to claim 1, characterized in that: The height fluctuation structure is a groove.

6. The compressor radial clearance measuring device according to claim 1, characterized in that: The compressor clearance measuring device also includes a control module connected to the optical fiber probe in real-time signal connection.

7. The compressor radial clearance measuring device according to claim 1, characterized in that: A plurality of height fluctuation structures are arranged on the surface of the rotor member.

8. A method for measuring radial clearance of a compressor, characterized in that: Using the compressor clearance measuring device according to any one of claims 1 to 7, the method comprises the following steps: The optical fiber probe is arranged in the stator of the compressor so that the optical fiber probe faces the surface of the rotor; The compressor is operated, and a plurality of groups of clearance data between the surface of the rotor component and the stator component are collected using an optical fiber probe, and the rotation parameters of the rotor component are obtained through the clearance data.

9. The compressor radial clearance measurement method according to claim 8, characterized in that: It is determined whether the plurality of sets of clearance data are within a clearance tolerance range to determine whether the rotor component is eccentric.

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