Gas compressor axial clearance measurement method and gas compressor design method
By measuring and calculating the deformation amount caused by load in the compressor, combined with conventional gap measurement methods, the front and rear gaps of the rotor in the operating state are accurately calculated, which solves the problem of inaccurate gap calculation in the prior art, prevents rotation and static grinding, and provides a basis for design optimization.
Patent Information
- Application Number
- CN202311156902.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-09-07
- Publication Date
- 2025-03-07
AI Technical Summary
The prior art is difficult to accurately calculate the axial gap of the compressor rotation and static cells, resulting in unreasonable gap values, which can easily cause rotation and static cells to bump.
By obtaining the concentrated loads under the static blades at each level of the compressor, using the loading tool to apply the load, measuring the distance change from the reference plane, calculating the deformation amount, and combining with conventional gap measurement methods, the front and rear gaps of the rotor in the operating state are calculated.
It effectively avoids the problem of inaccurate calculation and analysis, ensures the reasonable selection of the axial gap of the compressor, prevents rotation and static grinding, and provides a basis for optimization of the compressor design.
Smart Images
Figure CN119572519A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the field of aeroengine design, and in particular to a compressor axial clearance measurement method. Background Art
[0002] The setting of the axial clearance between the rotor and stator of an aircraft engine has an important impact on the safety performance of the engine. For a compressor, the axial clearance between the rotor and stator mainly refers to the clearance between the blade edge plate of each stage of the compressor and the inner ring of the stator.
[0003] like Figure 1 The schematic diagram of the configuration of the existing compressor is shown. As shown in the figure, the axial clearance includes the rotor front clearance Cq and the rotor rear clearance Ch. In the design stage of the aircraft engine, the rotor front clearance Cq and the rotor rear clearance Ch need to be designed within a reasonable value range. If the clearance is too large, it will lead to increased leakage and performance degradation. The reasonable selection of the axial clearance is currently a difficulty in the compressor design process.
[0004] When designing a compressor currently, the axial clearance between the rotor and the stator under various typical operating conditions is calculated and evaluated. However, the inventors have found that the existing calculation and analysis is difficult to simulate the actual situation, and the calculation deviation is large, resulting in unreasonable clearance values, which in turn causes rotor and stator friction. Summary of the invention
[0005] The object of the present invention is to provide a compressor axial clearance measurement method, which can effectively avoid rotor and stator rubbing accidents caused by inaccurate calculation of the compressor rotor and stator axial clearance.
[0006] A method for measuring the axial clearance of a compressor to achieve the above-mentioned purpose comprises:
[0007] Obtain the concentrated loads on each stage of the compressor stator row;
[0008] Place the compressor casing assembly vertically with the compressor intake side facing downward, and measure a first distance between the characteristic position and the reference plane along the axial direction of the compressor;
[0009] Installing a loading tool on the compressor casing, and causing the loading tool to apply a load according to the concentrated load;
[0010] measuring a second distance between the characteristic position and the reference plane along the axial direction of the compressor after the load is applied, and calculating a first deformation amount after the load is applied;
[0011] After removing the loading fixture, the compressor is turned over so that the air inlet side of the compressor faces upward, and a third distance between the characteristic position and the reference plane along the axial direction of the compressor is measured;
[0012] Installing the loading tool on the compressor casing, and causing the loading tool to apply a load according to the concentrated load;
[0013] measuring a third distance between the characteristic position and the reference plane along the axial direction of the compressor after the load is applied, and calculating a second deformation amount after the load is applied;
[0014] Measure the front clearance and rear clearance of each stage of the compressor rotor according to the conventional rotor and stator axial clearance measurement method;
[0015] The conventional clearance and the deformation measured by loading are superimposed, and the rotor front clearance in the operating state is calculated according to the rotor front clearance and the second deformation, and the rotor rear clearance in the operating state is calculated according to the rotor rear clearance and the second deformation.
[0016] In one or more embodiments, further comprising:
[0017] Calculate the first load of gas on each stage of compressor stator blades under extreme working conditions;
[0018] Calculate the second load of gas on the inner ring under extreme working conditions;
[0019] The concentrated load is the sum of the first load and the second load.
[0020] In one or more embodiments, the loading tool is designed according to the stator structure.
[0021] In one or more embodiments, the loading tool applying the load comprises:
[0022] A weight is installed on the loading fixture according to the concentrated load.
[0023] In one or more embodiments, the characteristic position is the front and rear edge of the stator inner ring edge plate.
[0024] In one or more embodiments, the reference surface is the front and rear mating end surfaces of the receiver.
[0025] On the other hand, according to some embodiments of the present application, a compressor design method is also provided, which adopts the compressor axial clearance measurement method as described above to obtain the rotor front clearance in the operating state and the rotor rear clearance in the operating state, and designs the compressor according to the rotor front clearance in the operating state and the rotor rear clearance in the operating state.
[0026] In one or more embodiments, further comprising:
[0027] Determine whether the rotor front clearance in the operating state or the rotor rear clearance in the operating state is 0. If so, grind the compressor parts and modify the compressor design.
[0028] In one or more embodiments, further comprising:
[0029] Set the gap threshold;
[0030] Determine the magnitude of the rotor front clearance in the running state and the rotor rear clearance in the running state relative to the clearance threshold;
[0031] If the rotor front clearance in the operating state or the rotor rear clearance in the operating state is greater than the clearance threshold, the compressor design is modified, and the rotor front clearance in the operating state or the rotor rear clearance in the operating state that is greater than the clearance threshold is reduced.
[0032] The beneficial effects of the present invention are:
[0033] Through this method, the aerodynamic load under extreme working conditions is equivalently applied to the inner ring of the stator blade through the tooling, so that the deformation of the inner ring of the stator blade can be intuitively simulated during the assembly process, avoiding the problem of inaccurate calculation and analysis, ensuring the reasonable selection of the compressor axial clearance, and effectively preventing the rotor and stator from rubbing against each other. It effectively solves the problem that the axial clearance between the rotor and stator of the compressor cannot be accurately calculated, which easily leads to the friction between the rotor and stator, and provides a basis for subsequent design optimization, providing strong support for the design of the bleed air to the compressor clearance.
[0034] The above description is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS
[0035] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Moreover, the same reference numerals are used throughout the drawings to represent the same components. In the drawings:
[0036] Figure 1 A schematic diagram of the configuration of an existing compressor is shown;
[0037] Figures 2 to 3 A schematic diagram of the measurement process according to the compressor axial clearance measurement method is shown. DETAILED DESCRIPTION
[0038] The following embodiments of the technical solution of the present application will be described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.
[0039] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.
[0040] Usually, when designing a compressor, the axial clearance between the rotor and the stator under various typical operating conditions is calculated and evaluated. However, the inventors found that since a bushing is installed between the blades and the casing, the bushing will deform when it is under load during operation. At the same time, there are gaps between the blades and the bushing, and between the bushing and the casing. This makes it difficult for the calculation and analysis to simulate the actual situation. The calculation deviation is large, resulting in unreasonable clearance values, which in turn causes the rotor and stator to rub against each other.
[0041] In order to solve the aforementioned problem, on the one hand, according to some embodiments of the present application, a method for measuring the axial clearance of a compressor is provided, which comprises the following steps:
[0042] First, the concentrated loads on each level of the compressor stator row are obtained;
[0043] Then, if Figure 2 As shown, the compressor casing assembly 1 is placed vertically, with the compressor intake side facing downward, and a first distance Di between the characteristic position K and the reference plane along the axial direction of the compressor is measured;
[0044] Installing a loading tool 2 on the compressor casing 1, and applying a load to the loading tool 2 according to the concentrated load;
[0045] Measuring a second distance Di' between the characteristic position and the reference plane along the axial direction of the compressor after the load is applied, and calculating a first deformation amount Δi after the load is applied, wherein the first deformation amount Δi refers to the deformation amount of each blade row when the aerodynamic load is forward;
[0046] After removing the loading tool 2, turn the compressor over so that Figure 3 As shown, the air inlet side of the compressor is placed upward, and the third distance di between the characteristic position K and the reference plane along the axial direction of the compressor is measured;
[0047] The loading tool 2 is installed on the compressor casing 1 again, and the loading tool applies a load according to the concentrated load order;
[0048] After the load is applied, the third distance di' between the characteristic position and the reference plane along the axial direction of the compressor is measured, and at the same time, the second deformation δi after the load is applied is calculated, and the second deformation δi refers to the deformation of each blade row when the aerodynamic load is backward;
[0049] Measure the front clearance Cqi and rear clearance Chi of the compressor rotors at each level according to the conventional rotor and stator axial clearance measurement method;
[0050] The conventional clearance and the deformation measured by loading are superimposed, and the front clearance of the rotor in the running state is calculated according to the front clearance of the rotor and the second deformation. The rear clearance of the rotor in the running state is calculated according to the rear clearance of the rotor and the second deformation. The calculation formula can be expressed as follows:
[0051] The rotor front clearance in the running state: C'qi = Cqi-δi;
[0052] The rotor rear clearance in the running state is: C'hi = Chi-Δi.
[0053] In the description of the embodiments of the present application, the technical terms "first", "second", etc. are only used to distinguish different objects, and cannot be understood as indicating or implying relative importance or implicitly indicating the number, specific order or primary and secondary relationship of the indicated technical features. In the description of the embodiments of the present application, the meaning of "multiple" is more than two, unless otherwise clearly and specifically defined.
[0054] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.
[0055] In one or more embodiments, the compressor axial clearance measurement method further includes:
[0056] Calculate the first load Fi of gas on each stage of compressor stator blades under extreme working conditions;
[0057] Calculate the second load Ni of the gas on the inner ring under extreme working conditions;
[0058] The concentrated load is the sum of the first load and the second load, that is, the concentrated load Gi=first load Fi+second load Ni.
[0059] In one or more embodiments, in the compressor axial clearance measurement method, the loading tool 2 is designed according to the stator structure.
[0060] In one or more embodiments, Figure 2 as well as Figure 3 As shown, the loading tooling applies the load including: installing a weight 4 on the loading tooling according to the concentrated load, and implementing the loading load through the weight 4.
[0061] In one or more embodiments, the characteristic position K is the front and rear edge of the stator inner ring rim plate. Through this design, more accurate measurement data can be obtained.
[0062] In one or more embodiments, the reference surface is the front and rear mating end surfaces of the receiver. Through this design, more accurate measurement data can be obtained.
[0063] On the other hand, according to some embodiments of the present application, a compressor design method is also provided, which adopts the compressor axial clearance measurement method described in one or more of the previous embodiments to obtain the rotor front clearance in the operating state and the rotor rear clearance in the operating state, and designs the compressor based on the rotor front clearance in the operating state and the rotor rear clearance in the operating state.
[0064] In one embodiment of the compressor design method, the compressor design method further includes:
[0065] Determine whether the rotor front clearance in the operating state or the rotor rear clearance in the operating state is 0. If so, grind the compressor parts and modify the compressor design.
[0066] In one embodiment of the compressor design method, the compressor design method further includes:
[0067] Setting a gap threshold, in a specific embodiment, the gap threshold is 2 to 5 mm;
[0068] Determine the magnitude of the rotor front clearance in the running state and the rotor rear clearance in the running state relative to the clearance threshold;
[0069] If the rotor front clearance in the operating state or the rotor rear clearance in the operating state is greater than the clearance threshold, the compressor design is modified, and the rotor front clearance in the operating state or the rotor rear clearance in the operating state that is greater than the clearance threshold is reduced.
[0070] Through the above method, the aerodynamic load under extreme working conditions is equivalently applied to the inner ring of the stator blade through the tooling, so that the deformation of the inner ring of the stator blade can be intuitively simulated during the assembly process, avoiding the problem of inaccurate calculation and analysis, ensuring the reasonable selection of the compressor axial clearance, and effectively preventing the rotor and stator from rubbing against each other. It effectively solves the problem that the axial clearance between the rotor and stator of the compressor cannot be accurately calculated, which easily leads to the friction between the rotor and stator, and provides a basis for subsequent design optimization, providing strong support for the design of the bleed air to the compressor clearance.
[0071] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application, and they should all be included in the scope of the claims and specification of the present application. In particular, as long as there is no structural conflict, the various technical features mentioned in the various embodiments can be combined in any way. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions that fall within the scope of the claims.
Claims
1. A method for measuring the axial clearance of a compressor, characterized in that: include: Obtain the concentrated loads on each stage of the compressor stator row; Place the compressor casing assembly vertically with the compressor intake side facing downward, and measure a first distance between the characteristic position and the reference plane along the axial direction of the compressor; Installing a loading tool on the compressor casing, and causing the loading tool to apply a load according to the concentrated load; measuring a second distance between the characteristic position and the reference plane along the axial direction of the compressor after the load is applied, and calculating a first deformation amount after the load is applied; After removing the loading fixture, the compressor is turned over so that the air inlet side of the compressor faces upward, and a third distance between the characteristic position and the reference plane along the axial direction of the compressor is measured; Installing the loading tool on the compressor casing, and causing the loading tool to apply a load according to the concentrated load; measuring a third distance between the characteristic position and the reference plane along the axial direction of the compressor after the load is applied, and calculating a second deformation amount after the load is applied; Measure the front clearance and rear clearance of each stage of the compressor rotor according to the conventional rotor and stator axial clearance measurement method; The conventional clearance and the deformation measured by loading are superimposed, and the rotor front clearance in the operating state is calculated according to the rotor front clearance and the second deformation, and the rotor rear clearance in the operating state is calculated according to the rotor rear clearance and the second deformation.
2. The compressor axial clearance measurement method according to claim 1, characterized in that: Also includes: Calculate the first load of gas on each stage of compressor stator blades under extreme working conditions; Calculate the second load of gas on the inner ring under extreme working conditions; The concentrated load is the sum of the first load and the second load.
3. The compressor axial clearance measurement method according to claim 1, characterized in that: The loading tooling is designed according to the stator structure.
4. The compressor axial clearance measurement method according to claim 1, characterized in that: The loading tooling applies the load including: A weight is installed on the loading fixture according to the concentrated load.
5. The compressor axial clearance measurement method according to claim 1, characterized in that: The characteristic position is the front and rear edge of the stator inner ring rim plate.
6. The compressor axial clearance measurement method according to claim 1, characterized in that: The reference surface is the front and rear mating end surfaces of the receiver.
7. A compressor design method, characterized in that: The compressor axial clearance measurement method as described in any one of claims 1 to 6 is used to obtain the rotor front clearance in the operating state and the rotor rear clearance in the operating state, and the compressor is designed according to the rotor front clearance in the operating state and the rotor rear clearance in the operating state.
8. The compressor design method according to claim 7, characterized in that: Also includes: Determine whether the rotor front clearance in the operating state or the rotor rear clearance in the operating state is 0. If so, grind the compressor parts and modify the compressor design.
9. The compressor design method according to claim 7, characterized in that: Also includes: Set the gap threshold; Determine the magnitude of the rotor front clearance in the running state and the rotor rear clearance in the running state relative to the clearance threshold; If the rotor front clearance in the operating state or the rotor rear clearance in the operating state is greater than the clearance threshold, the compressor design is modified, and the rotor front clearance in the operating state or the rotor rear clearance in the operating state that is greater than the clearance threshold is reduced.