A multi-point dynamic total pressure measurement structure for a distorted flow field in a compressor inlet casing

Abstract

The application belongs to the technical field of design of multi-point dynamic total pressure measurement of distorted flow field in compressor inlet casing, and particularly relates to a kind of multi-point dynamic total pressure measurement structure of distorted flow field in compressor inlet casing, which can realize accurate measurement of multi-point dynamic total pressure of distorted flow field in compressor inlet casing under the condition of guaranteeing the original structure of compressor inlet casing in aero-engine, has relatively small windward area, can avoid great influence on compressor performance, and can be reliably and conveniently fixed on the casing, so that the possibility of danger can be reduced.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of design of multi-point dynamic total pressure measurement of a distorted flow field in a compressor inlet casing, and particularly relates to a multi-point dynamic total pressure measurement structure of a distorted flow field in a compressor inlet casing. BACKGROUND

[0002] In a stability test of an aero-engine compressor, a distorted flow field needs to be constructed in the compressor inlet casing, and a distorted index of the distorted flow field is obtained through multi-point dynamic total pressure measurement of the distorted flow field, so as to correlate the distorted index with a compressor stability index to describe the stability of the compressor.

[0003] With the current multi-point dynamic total pressure measurement structure, the measurement structure has the problem of mutual influence between each measurement point, affecting the measurement accuracy, and the measurement structure has a large windward area, affecting the performance of the compressor, in addition, the measurement structure is installed on the inner surface of the casing, which has a large safety hazard.

[0004] The present application is proposed in view of the above technical defects.

[0005] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide a multi-point dynamic total pressure measurement structure of a distorted flow field in a compressor inlet casing to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] A multi-point dynamic total pressure measurement structure of a distorted flow field in a compressor inlet casing, comprising:

[0009] A mounting seat having a protruding part inserted into a measurement hole on the casing, and the mounting seat has a circular hole with an opening in the circumferential direction of the casing;

[0010] A support rod having a runway-shaped section at one end, a rectangular section at the other end, and a cylindrical section in the middle, wherein the runway-shaped section has a plurality of axial pressure sensing holes on the leading edge and a strip-shaped groove in communication with each pressure sensing hole on the trailing edge; the rectangular section and the cylindrical section have lead hole in communication with the strip-shaped groove;

[0011] A plurality of fairings, in the shape of a cylinder, with an inner wall having a plurality of circumferentially distributed stop protrusions, one end welded in each pressure sensing hole, the other end with a 90° chamfered end, and the side wall of the end having a plurality of circumferentially distributed flow holes;

[0012] A plurality of dynamic pressure sensors, with heads extending into each fairing;

[0013] A pressure strip, with one side edge having a plurality of notches, each notch clamping the lead of each dynamic pressure sensor; the pressure strip is fastened in the strip-shaped groove by a plurality of screws and spring washers, and the heads of each dynamic pressure sensor are pressed tightly in the fairing;

[0014] A plurality of asbestos gaskets, arranged in each fairing, between the head of each dynamic pressure sensor and the pressure strip;

[0015] A plug strip, welded on the support rod, plugging the strip-shaped groove; the protruding end of each fairing on the runway-shaped section is opposite the gap and extends into the casing through the circular hole; the cylindrical section is inserted into the circular hole and rotated 90°, and each dynamic pressure sensor is opposite the incoming flow direction in the casing; the mounting seat and the rectangular section are fixed on the casing by screws;

[0016] An adapter cylinder, one end welded on the rectangular section, with an open side wall;

[0017] An adapter seat, welded on the other end of the adapter cylinder, with an adapter hole thereon;

[0018] An electrical connector, connected to the adapter seat by screws and washers; the leads of each dynamic pressure sensor are connected to the electrical connector through the strip-shaped groove, the lead hole, the adapter cylinder, and the adapter hole; the compensation module on the lead of each dynamic pressure sensor is located in the adapter cylinder;

[0019] An adapter, connected to the electrical connector, converting the electrical interface of the electrical connector into an aviation pin for easy connection to a data acquisition system for data acquisition;

[0020] An asbestos rope, filled into the adapter cylinder through the opening, fixing the compensation module on the lead of each dynamic pressure sensor;

[0021] A cover plate, welded on the adapter cylinder, plugging the opening.

[0022] According to at least one embodiment of the present application, in the above-mentioned multi-point dynamic total pressure measurement structure in the distorted flow field in the inlet casing of the compressor, the adapter cylinder is rectangular, the opening at one end of the rectangular section is rectangular, and the opening at one end of the adapter seat is circular;

[0023] The adapter seat has a cylindrical protrusion inserted into the adapter cylinder.

[0024] According to at least one embodiment of the present application, the multi-point dynamic total pressure measurement structure for the distorted flow field in the compressor inlet casing further comprises:

[0025] The mounting seat gasket is arranged between the mounting seat and the casing.

[0026] The support rod gasket is arranged between the rectangular section and the mounting seat gasket.

[0027] The present application has at least the following beneficial technical effects:

[0028] The present application provides a multi-point dynamic total pressure measurement structure for the distorted flow field in the compressor inlet casing, which can accurately measure the multi-point dynamic total pressure of the distorted flow field in the compressor inlet casing while ensuring the original structure of the casing at the compressor inlet in the aero-engine, has a relatively small windward area, can avoid affecting the compression performance, can be reliably and conveniently fixed on the casing, and can reduce the possibility of danger. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 is a schematic view of the multi-point dynamic total pressure measurement structure for the distorted flow field in the compressor inlet casing provided by the present application;

[0030] Figure 2 is an A-A view of Figure 1

[0031] Figure 3 is a B view of Figure 1

[0032] Figure 4 is a schematic view of the fairing provided by the present application;

[0033] Figure 5 is a C view of Figure 4

[0034] Figure 6 is a schematic view of the compression strip provided by the present application;

[0035] Figure 7 is a schematic view of the asbestos gasket provided by the present application;

[0036] Figure 8 is a three-view of the adapter cylinder provided by the present application;

[0037] Figure 9 is a three-view of the adapter seat provided by the present application;

[0038] Figure 10 is a schematic view of the multi-point dynamic total pressure measurement structure for the distorted flow field in the compressor inlet casing provided by the present application, in which the mounting seat is removed;

[0039] ​​​Figure 11 is Figure 10 a D-D schematic view of;

[0040] wherein:

[0041] 1 - mounting base; 2 - strut; 3 - fairing; 4 - mounting base gasket; 5 - strut gasket; 6 - dynamic pressure sensor; 7 - baffle; 8 - asbestos gasket; 9 - baffle; 10 - adapter cylinder; 11 - adapter base; 12 - electrical connector; 13 - adapter; 14 - asbestos rope; 15 - cover plate.

[0042] In order to better illustrate the embodiments, some components in the drawings can be omitted, enlarged or reduced, and do not represent the actual size of the product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0043] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described in detail below in combination with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0044] In addition, unless otherwise defined, the technical terms or scientific terms used in the present application description should be the general meaning understood by the general technical personnel in the field to which the present application belongs. The words such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the present application description only indicate the relative direction or positional relationship, and not the specific orientation of the device or element, and the relative positional relationship can also change accordingly when the absolute position of the described object changes, therefore, it cannot be understood as a limitation of the present application. The "first", "second", "third" and the like used in the present application description are only for the purpose of description, in order to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "a" or "the" and the like used in the present application description should not be understood as an absolute limitation on the quantity, but should be understood as the existence of at least one. The "include" or "contain" and the like used in the present application description means that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and do not exclude other elements or objects.

[0045] In addition, it needs to be explained that, unless otherwise explicitly specified and limited, the similar words such as'mount', 'connect', 'link' and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection, or detachable connection, or integrally connected; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and the person skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0046] The measuring hole on the casing at the inlet of the existing aero-engine compressor is strip-shaped, and the length direction of the strip-shaped hole is perpendicular to the axial direction of the compressor. In order to maintain the original structure of the casing, the strip-shaped measuring hole on the casing is not changed. The embodiment of the present application provides a kind of multi-point dynamic total pressure measurement structure of distortion flow field in compressor inlet casing. The following will be described in detail with reference to the accompanying drawings Figures 1 to 11 Further detailed description.

[0047] A kind of multi-point dynamic total pressure measurement structure of distortion flow field in compressor inlet casing, comprising:

[0048] Mounting seat 1, with protruding part on it, the protruding part is inserted into the measuring hole on the casing, and the mounting seat 1 has a circular hole, and the circular hole has an aperture, and the aperture is in the circumferential direction of the casing;

[0049] Supporting rod 2, one end is runway type section, the other end is rectangular section, and the middle part is cylindrical section, wherein the leading edge of the runway type section has a plurality of axial distribution pressure holes, and the trailing edge has a strip-shaped slot communicated with each pressure hole;Rectangular section, cylindrical section has lead hole communicated with strip-shaped slot;

[0050] A plurality of fairing 3, in the form of a cylinder, with a plurality of stop protrusions distributed in the circumferential direction on the inner wall, one end is welded in each pressure hole, and the other end is chamfered 90°, and the side wall of the end has a plurality of circumferential distribution flow holes;

[0051] A plurality of dynamic pressure sensors 6, the head portion extends into each fairing 3;

[0052] Compression strip 7, one side edge has a plurality of notches, each notch is clamped on the lead wire of each dynamic pressure sensor 6;Compression strip 7 is fastened in strip-shaped slot by a plurality of screws and spring washers, and the head portion of each dynamic pressure sensor 6 is pressed in the fairing 3;

[0053] A plurality of asbestos gaskets 8 are arranged in each fairing 3, and are arranged between the head portion of each dynamic pressure sensor 6 and the compression strip 7;

[0054] The blocking strip 9 is welded on the supporting rod 2 to block the strip-shaped slot. The protruding end of each dome 3 on the runway-shaped section is opposite to the gap and passes through the circular hole to extend into the casing. The cylindrical section is inserted into the circular hole and is rotated by 90°. Each dynamic pressure sensor 6 is opposite to the direction of the incoming flow in the casing. The mounting seat 1 and the rectangular section are fixed on the casing by screws.

[0055] The adapter cylinder 10 is welded on one end of the rectangular section and has an opening on the side wall.

[0056] The adapter seat 11 is welded on the other end of the adapter cylinder 10 and has an adapter hole thereon.

[0057] The electrical connector 12 is connected to the adapter seat 11 by screws and a gasket. The lead wires of each dynamic pressure sensor 6 pass through the strip-shaped slot, the lead wire hole, the adapter cylinder 10 and the adapter hole to be connected to the electrical connector 12. The compensation module on the lead wire of each dynamic pressure sensor 6 is located in the adapter cylinder 10.

[0058] The adapter 13 is connected to the electrical connector 12 to convert the electrical interface of the electrical connector 12 into an aviation pin.

[0059] The asbestos rope 14 is filled into the adapter cylinder 10 through the opening to fix the compensation module on the lead wire of each dynamic pressure sensor 6.

[0060] The cover plate 15 is welded on the adapter cylinder 10 to block the opening.

[0061] For the multi-point dynamic total pressure measurement structure of the distorted flow field in the inlet casing of the compressor disclosed in the above embodiment, it can be understood by those skilled in the art that the mounting seat 1 is designed to block the measurement hole on the casing through the protruding part, and the mounting seat 1 has a circular hole with a gap in the circumferential direction of the casing. In this way, the protruding end of each dome 3 on the runway-shaped section of the supporting rod 2 can pass through the circular hole and extend into the casing without changing the original measurement hole on the casing and maintaining the original structure of the casing. By rotating by 90°, each dynamic pressure sensor 6 is opposite to the direction of the incoming flow in the casing to ensure the accuracy of the multi-point measurement of the dynamic total pressure of the distorted flow field in the inlet casing of the compressor. In addition, the mounting seat 1 and the rectangular section on the supporting rod 2 are fixed on the casing by screws to reliably fix the entire measurement structure on the casing, thereby reducing the possibility of danger.

[0062] For the above-mentioned embodiment disclosed in the compressor inlet casing inside the distorted flow field multi-point dynamic total pressure measurement structure, those skilled in the art can understand that the design of the 90° chamfer at the end of each fairing 3 can play a role in converging the airflow, which can increase the insensitive angle of the dynamic pressure sensor 6 test, and ensure the accuracy of the dynamic total pressure multi-point measurement of the distorted flow field in the compressor inlet casing. In addition, the design of the multiple stop protrusions on the inner wall of each fairing 3 can effectively prevent the head of the dynamic pressure sensor 6 from being pulled out, and will not block the airflow, ensuring the accuracy of the measurement results.

[0063] For the above-mentioned embodiment disclosed in the compressor inlet casing inside the distorted flow field multi-point dynamic total pressure measurement structure, those skilled in the art can understand that the design of the 90° chamfer at the end of each fairing 3 can play a role in converging the airflow, which can increase the insensitive angle of the dynamic pressure sensor 6 test, and ensure the accuracy of the dynamic total pressure multi-point measurement of the distorted flow field in the compressor inlet casing. In addition, the design of the multiple stop protrusions on the inner wall of each fairing 3 can effectively prevent the head of the dynamic pressure sensor 6 from being pulled out, and will not block the airflow, ensuring the accuracy of the measurement results.

[0064] For the above-mentioned embodiment disclosed in the compressor inlet casing inside the distorted flow field multi-point dynamic total pressure measurement structure, those skilled in the art can understand that the design of the 90° chamfer at the end of each fairing 3 can play a role in converging the airflow, which can increase the insensitive angle of the dynamic pressure sensor 6 test, and ensure the accuracy of the dynamic total pressure multi-point measurement of the distorted flow field in the compressor inlet casing. In addition, the design of the multiple stop protrusions on the inner wall of each fairing 3 can effectively prevent the head of the dynamic pressure sensor 6 from being pulled out, and will not block the airflow, ensuring the accuracy of the measurement results.

[0065] For the above-mentioned embodiment disclosed in the compressor inlet casing inside the distorted flow field multi-point dynamic total pressure measurement structure, those skilled in the art can understand that the design of the 90° chamfer at the end of each fairing 3 can play a role in converging the airflow, which can increase the insensitive angle of the dynamic pressure sensor 6 test, and ensure the accuracy of the dynamic total pressure multi-point measurement of the distorted flow field in the compressor inlet casing. In addition, the design of the multiple stop protrusions on the inner wall of each fairing 3 can effectively prevent the head of the dynamic pressure sensor 6 from being pulled out, and will not block the airflow, ensuring the accuracy of the measurement results.

[0066] In some optional embodiments, the above-mentioned compressor inlet casing inside the distorted flow field multi-point dynamic total pressure measurement structure, the adapter cylinder 10 is rectangular, the opening towards one end of the rectangular section is rectangular, and the opening towards one end of the adapter seat 11 is circular.

[0067] The adapter seat 11 has a cylindrical protrusion, which is inserted into the adapter cylinder 10 and cooperates with the circular opening to reliably connect the adapter seat 11 and the adapter cylinder 10.

[0068] In some alternative embodiments, the multi-point dynamic total pressure measurement structure for distorted flow field in the compressor inlet casing further comprises:

[0069] The mounting seat gasket 4 is arranged between the mounting seat 1 and the casing to seal.

[0070] The supporting rod gasket 5 is arranged between the rectangular section and the mounting seat gasket 4 to enhance the sealing effect.

[0071] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other.

[0072] The technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. It should be understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the related technical features. The technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A multi-point dynamic total pressure measurement configuration in a distorted flow field within a compressor inlet casing, characterized by, The application relates to a multi-point dynamic total pressure measuring structure for a distorted flow field in a compressor inlet casing, which comprises the following components: a mounting base (1) with a convex part inserted into a measuring hole in the casing and a circular hole with a gap in the circumferential direction of the casing; a support rod (2) with a runway-shaped section at one end, a rectangular section at the other end and a cylindrical section in the middle, wherein the front edge of the runway-shaped section is provided with a plurality of axial pressure holes, and the rear edge is provided with a strip-shaped slot communicated with the pressure holes; the rectangular section and the cylindrical section are provided with lead holes communicated with the strip-shaped slot; a plurality of fairings (3) in the shape of a cylinder, the inner wall of which is provided with a plurality of circumferential stop protrusions, one end of which is welded in each pressure hole, and the other end is chamfered by 90 degrees, and the side wall of the end is provided with a plurality of circumferential flow holes; a plurality of dynamic pressure sensors (6) with heads inserted into each fairing (3); a pressing strip (7) with a plurality of notches on one side edge, each notch being clamped on the lead wire of each dynamic pressure sensor (6); the pressing strip (7) is fastened in the strip-shaped slot through a plurality of screws and spring washers, and the heads of the dynamic pressure sensors (6) are pressed in the fairing (3); a plurality of asbestos gaskets (8) arranged in each fairing (3) and arranged between the heads of the dynamic pressure sensors (6) and the pressing strip (7); a blocking strip (9) welded on the support rod (2) to block the strip-shaped slot; the convex end of each fairing (3) on the runway-shaped section is opposite the gap and passes through the circular hole to extend into the casing; the cylindrical section is inserted into the circular hole and rotated by 90 degrees, and each dynamic pressure sensor (6) is opposite the direction of the incoming flow in the casing; the mounting base (1) and the rectangular section are fixed on the casing through screws; an adapter cylinder (10) welded at one end on the rectangular section and provided with an opening on the side wall; an adapter base (11) welded at the other end of the adapter cylinder (10) and provided with an adapter hole; an electrical connector (12) connected to the adapter base (11) through screws and washers; the lead wires of each dynamic pressure sensor (6) pass through the strip-shaped slot, the lead hole, the adapter cylinder (10) and the adapter hole to be connected to the electrical connector (12); the compensation module on the lead wire of each dynamic pressure sensor (6) is located in the adapter cylinder (10); an adapter (13) connected to the electrical connector (12) to convert the electrical interface of the electrical connector (12) into an aviation pin; an asbestos rope (14) filled into the adapter cylinder (10) through the opening to fix the compensation module on the lead wire of each dynamic pressure sensor (6); a cover plate (15) welded on the adapter cylinder (10) to block the opening.

2. The multi-point dynamic total pressure measuring structure for a distorted flow field in a compressor inlet casing according to claim 1, wherein the adapter cylinder (10) is in the shape of a rectangle, the opening at one end of the rectangular section is in the shape of a rectangle, and the opening at the other end of the adapter base (11) is in the shape of a circle; the adapter base (11) is provided with a cylindrical protrusion inserted into the adapter cylinder (10).

3. The multi-point dynamic total pressure measuring structure for a distorted flow field in a compressor inlet casing according to claim 1, further comprising: a mounting base gasket (4) arranged between the mounting base (1) and the casing. ​ ​ ​ Supporting rod gasket (5), gasket between rectangular section, mounting seat gasket (4).

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