An intermediate casing test lead structure for aircraft engine fan testing

Abstract

The present application belongs to the technical field of aircraft engine fan testing, and specifically relates to an intermediate casing test lead structure for aircraft engine fan testing. It can be understood by technicians in the field that the diverter ring is designed to be a hollow structure. On the one hand, it can reduce the mass of the intermediate casing and improve the loading efficiency. On the other hand, it cooperates with the design of the outer wall measurement cover plate and the inner wall measurement cover plate, as well as the design of the lead holes and channels on the outer casing, support plate and other components to realize the installation and lead-in of the outer wall measurement sensor and the inner wall measurement sensor, and facilitate the measurement of the temperature and pressure at the inner and outer walls of the diverter ring.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine fan testing, and in particular relates to an intermediate casing test lead structure for aircraft engine fan testing. Background Art

[0002] In the aircraft engine fan test, the intermediate casing is connected between the fan and the exhaust casing. It is the main force transmission frame of the test, transferring the load transmitted by the fulcrum to the exhaust casing and the test bench. It mainly includes an outer casing, an inner casing, a diverter ring and multiple support plates. Among them, the inner casing is arranged inside the outer casing, and each support plate is supported circumferentially between the outer casing and the inner casing. The diverter ring is connected to the trailing edge of each support plate, forming an outer containment with the outer casing and an inner containment with the inner casing.

[0003] In aircraft engine fan testing, the intermediate casing separates the compressed air from the fan into two streams, an outer and inner flow, which are then discharged through the exhaust casing. However, the current intermediate casing has the following defects:

[0004] 1) During the aircraft engine fan test, the temperature and pressure on the inner and outer walls of the diverter ring are measured, and it is inconvenient to wire the temperature and pressure sensors;

[0005] 2) The outer casing, inner casing, support plate and diverter ring are solid structures, which are heavy and affect the loading efficiency.

[0006] This application is proposed in view of the above-mentioned technical defects.

[0007] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of the present application. In the absence of clear evidence that the above content has been disclosed on the filing date of the present application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the Invention

[0008] The purpose of the present application is to provide an intermediate casing test lead structure for aircraft engine fan testing, so as to overcome or alleviate at least one of the existing technical defects.

[0009] The technical solution of this application is:

[0010] An intermediate casing test lead structure for aircraft engine fan testing, comprising:

[0011] an outer receiver having an outer receiver lead hole;

[0012] an inner receiver, disposed within the outer receiver;

[0013] A plurality of support plates are supported circumferentially between the outer casing and the inner casing, wherein one of the support plates has a support plate lead channel, one end of the support plate lead channel is connected to the lead hole of the outer casing;

[0014] The diverter ring is connected to the rear edge of each support plate, has a hollow structure, is connected to the other end of the support plate lead channel, and has a diverter ring lead hole at the rear edge directly opposite the support plate with the support plate lead channel; the diverter ring has an outer wall measurement area, an outer wall measurement mounting groove is provided on the outer wall of the outer wall measurement area, and an outer wall measurement lead hole is provided on the rear edge; the diverter ring has an inner wall measurement area, an inner wall measurement mounting groove is provided on the outer wall of the inner wall measurement area, an inner wall measurement lead hole is provided on the rear edge, and multiple inner wall measurement mounting holes are provided on the inner wall;

[0015] An outer wall measurement cover plate is connected to the outer wall measurement installation groove and has a plurality of outer wall measurement installation holes;

[0016] Multiple outer wall measurement sensors are installed in each outer wall measurement installation hole, and their leads are led out through the outer wall measurement lead hole, the diverter ring lead hole, the support plate lead channel, and the outer casing lead hole;

[0017] An inner wall measurement cover plate is connected to the inner wall measurement installation groove;

[0018] Multiple inner wall measurement sensors are installed in each inner wall measurement installation hole, and their leads are led out through the inner wall measurement lead hole, the diverter ring lead hole, the support plate lead channel, and the outer casing lead hole.

[0019] According to at least one embodiment of the present application, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the outer casing, inner casing, support plate, and diverter ring are an integrally formed structure.

[0020] According to at least one embodiment of the present application, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, a stopper is used to position the front end of the outer wall measurement cover plate against the front end of the outer wall measurement mounting slot, and the rear end has an inward folded edge. The inward folded edge is connected to the rear edge of the diverter ring located in the outer wall measurement area by bolts, and a spring washer is placed on the bolt. In addition, the inward folded edge has a lead lead hole for leading out the leads of each outer wall measurement sensor;

[0021] The front end of the inner wall measurement cover plate and the front end of the inner wall measurement mounting groove are positioned by a stop, and the rear end has an inward folded edge. The inward folded edge is connected to the rear edge of the diverter ring located in the inner wall measurement area by bolts, and a spring washer is padded on the bolt. In addition, the inward folded edge has a lead-out hole for leading out the leads of each inner wall measurement sensor.

[0022] According to at least one embodiment of the present application, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the thickness of the outer wall measurement cover plate is greater than the thickness of the outer wall of the diverter ring;

[0023] The thickness of the inner wall of the diverter ring in the measuring area of ​​the inner wall is greater than the thickness of the inner wall of the rest of the diverter ring.

[0024] According to at least one embodiment of the present application, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the outer wall measurement area on the diverter ring and its corresponding outer wall measurement cover plate and outer wall measurement sensor are distributed in multiple locations;

[0025] The inner wall measuring areas and the corresponding inner wall measuring covers and inner wall measuring sensors are distributed in multiple places on the diverter ring.

[0026] According to at least one embodiment of the present application, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the outer wall of the diverter ring has multiple assembly areas, and the outer wall located in the assembly area has assembly installation grooves;

[0027] The intermediate casing test lead structure for aircraft engine fan testing further includes:

[0028] Multiple assembly cover plates are connected in each assembly installation slot. The front end is positioned with the front end of the assembly installation slot by a stop. The rear end has an inward folded edge. The inward folded edge is connected to the rear edge of the diverter ring located in the assembly area by bolts, and spring washers are padded on the bolts. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1-Figure 4 This is a partial schematic diagram of the structure of the intermediate casing test lead for an aircraft engine fan test provided by an embodiment of the present application;

[0030] in:

[0031] 1-outer casing; 2-inner casing; 3-support plate; 4-diverter ring; 5-outer wall measurement cover; 6-outer wall measurement sensor; 7-inner wall measurement cover; 8-inner wall measurement sensor; 9-assembly cover.

[0032] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0033] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0034] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0035] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0036] The following is combined with Figures 1 to 4 This application is described in further detail.

[0037] An intermediate casing test lead structure for aircraft engine fan testing, comprising:

[0038] An outer receiver 1 having an outer receiver lead hole;

[0039] An inner casing 2 is arranged inside the outer casing 1;

[0040] A plurality of support plates 3 are supported circumferentially between the outer casing 1 and the inner casing 2, wherein one of the support plates 3 has a support plate lead channel, one end of which is connected to the lead hole of the outer casing;

[0041] The diverter ring 4 is connected to the rear edge of each support plate 3 and has a hollow structure. It is connected to the other end of the support plate lead channel. The rear edge has a diverter ring lead hole at the position of the support plate 3 with the support plate lead channel. The diverter ring 4 has an outer wall measurement area, an outer wall measurement mounting groove is provided on the outer wall of the outer wall measurement area, and an outer wall measurement lead hole is provided on the rear edge. The diverter ring has an inner wall measurement area, an inner wall measurement mounting groove is provided on the outer wall of the inner wall measurement area, an inner wall measurement lead hole is provided on the rear edge, and multiple inner wall measurement mounting holes are provided on the inner wall.

[0042] The outer wall measurement cover plate 5 is connected to the outer wall measurement installation groove and has a plurality of outer wall measurement installation holes;

[0043] Multiple outer wall measurement sensors 6 are installed in each outer wall measurement installation hole, and their leads are led out through the outer wall measurement lead hole, the diverter ring lead hole, the support plate lead channel, and the outer casing lead hole, such as Figure 2 、 Figure 4 As shown, the sheet can be pressed onto the trailing edge of the diverter ring 4 along the way;

[0044] Inner wall measurement cover plate 7, connected to the inner wall measurement installation groove;

[0045] Multiple inner wall measurement sensors 8 are installed in each inner wall measurement installation hole, and their leads are led out through the inner wall measurement lead hole, the diverter ring lead hole, the support plate lead channel, and the outer casing lead hole, such as Figure 3 、 Figure 4 As shown, the sheet can be pressed onto the trailing edge of the diverter ring 4 along the way.

[0046] As for the intermediate casing test lead structure for aircraft engine fan testing disclosed in the above embodiment, it can be understood by those skilled in the art that the design of the diverter ring 4 is a hollow structure. On the one hand, it can reduce the mass of the intermediate casing and improve the loading efficiency. On the other hand, it cooperates with the design of the outer wall measurement cover plate 5 and the inner wall measurement cover plate 7, as well as the design of the lead holes and channels on the outer casing 1, the support plate 3 and other components to realize the installation and lead-in of the outer wall measurement sensor 6 and the inner wall measurement sensor 8, and facilitate the measurement of the temperature and pressure at the inner and outer wall surfaces of the diverter ring 4.

[0047] In some optional embodiments, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the outer casing 1, the inner casing 2, the support plate 3, and the diverter ring 4 are an integrally formed structure.

[0048] In some optional embodiments, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the front end of the outer wall measurement cover plate 5 is positioned between the front end of the outer wall measurement mounting groove by a stop, and the rear end has an inward folded edge. The inward folded edge is connected to the trailing edge of the diverter ring 4 located in the outer wall measurement area by bolts, and a spring washer is placed on the bolt. In addition, the inward folded edge has a lead lead hole for leading out the leads of each outer wall measurement sensor 6;

[0049] The front end of the inner wall measurement cover plate 7 is positioned with the front end of the inner wall measurement mounting groove by a stop, and the rear end has an inward folded edge. The inward folded edge is connected to the rear edge of the diverter ring 4 located in the inner wall measurement area by bolts, and a spring washer is padded on the bolt. In addition, the inward folded edge has a lead-out hole for leading out the leads of each inner wall measurement sensor 8.

[0050] In some optional embodiments, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the thickness of the outer wall measurement cover plate 5 is greater than the thickness of the outer wall of the diverter ring 4, so as to have higher strength;

[0051] The thickness of the inner wall of the diverter ring 4 located in the inner wall measurement area is greater than the thickness of the inner wall of the other parts of the diverter ring 4, so as to have higher strength.

[0052] In some optional embodiments, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the outer wall measurement area on the diverter ring 4 and its corresponding outer wall measurement cover plate 5 and outer wall measurement sensor 6 are distributed in multiple locations, which can be located between two adjacent support plates 3. The specific number and distribution position can be determined by relevant technicians according to specific actual conditions when applying this application, and no further detailed description is given here.

[0053] There are multiple inner wall measurement areas on the diverter ring 4 and their corresponding inner wall measurement cover plates 7 and inner wall measurement sensors 8, which can be located between two adjacent support plates 3. The specific number and distribution positions can be determined by relevant technical personnel based on specific actual conditions when applying this application, and no further detailed explanation will be given here.

[0054] In some optional embodiments, in the above-mentioned intermediate casing test lead structure for aircraft engine fan testing, the outer wall of the diverter ring 4 has multiple assembly areas, and the outer wall located in the assembly area has assembly installation grooves;

[0055] The intermediate casing test lead structure for aircraft engine fan testing further includes:

[0056] Multiple assembly cover plates 9 are connected to each assembly installation groove, with the front end positioned between the front end of the assembly installation groove and the rear end having an inward folding edge, which is connected to the rear edge of the diverter ring 4 located in the assembly area by bolts, and spring washers are placed on the bolts, such as Figure 1 As shown, the assembly cover plate 9 and its assembly installation groove can be specifically located between two adjacent support plates 3. The specific number and distribution position can be determined by relevant technical personnel based on specific actual conditions when applying this application, and no further detailed explanation will be given here.

[0057] The various 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 various embodiments can be referred to in detail.

[0058] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. An intermediate casing test lead structure for aircraft engine fan testing, characterized in that: include: An outer casing (1) having an outer casing lead hole; An inner casing (2) is arranged inside the outer casing (1); A plurality of support plates (3) are supported circumferentially between the outer casing (1) and the inner casing (2), wherein one of the support plates (3) has a support plate lead channel, one end of the support plate lead channel being connected to the lead hole of the outer casing; The diverter ring (4) is connected to the rear edge of each support plate (3), is a hollow structure, is connected to the other end of the support plate lead channel, and has a diverter ring lead hole at the rear edge facing the support plate (3) having the support plate lead channel; the diverter ring (4) has an outer wall measurement area, an outer wall measurement installation groove is provided on the outer wall of the outer wall measurement area, and an outer wall measurement lead hole is provided on the rear edge; the diverter ring has an inner wall measurement area, an inner wall measurement installation groove is provided on the outer wall of the inner wall measurement area, an inner wall measurement lead hole is provided on the rear edge, and a plurality of inner wall measurement installation holes are provided on the inner wall; An outer wall measurement cover plate (5) is connected to the outer wall measurement installation groove and has a plurality of outer wall measurement installation holes; A plurality of outer wall measurement sensors (6) are installed in each outer wall measurement installation hole, and their leads are led out through the outer wall measurement lead hole, the diverter ring lead hole, the support plate lead channel, and the outer casing lead hole; An inner wall measurement cover plate (7) is connected to the inner wall measurement installation groove; A plurality of inner wall measurement sensors (8) are installed in each inner wall measurement installation hole, and their leads are led out through the inner wall measurement lead hole, the diverter ring lead hole, the support plate lead channel, and the outer casing lead hole.

2. The intermediate casing test lead structure for aircraft engine fan testing according to claim 1, characterized in that: The outer casing (1), the inner casing (2), the support plate (3), and the diverter ring (4) are an integrally formed structure.

3. The intermediate casing test lead structure for aircraft engine fan testing according to claim 1, characterized in that: The front end of the outer wall measurement cover plate (5) is positioned with the front end of the outer wall measurement installation groove by a stop, and the rear end has an inward folded edge. The inward folded edge is connected to the rear edge of the diverter ring (4) located in the outer wall measurement area by bolts, and a spring washer is placed on the bolt. In addition, the inward folded edge has a lead lead hole for leading out the lead wires of each outer wall measurement sensor (6); The front end of the inner wall measurement cover plate (7) is positioned with the front end of the inner wall measurement installation groove by a stop, and the rear end has an inward folded edge. The inward folded edge is connected to the rear edge of the diverter ring (4) located in the inner wall measurement area by bolts, and a spring washer is placed on the bolt. In addition, the inward folded edge has a lead lead hole for leading out the lead wires of each inner wall measurement sensor (8).

4. The intermediate casing test lead structure for aircraft engine fan testing according to claim 1, characterized in that: The thickness of the outer wall measuring cover plate (5) is greater than the thickness of the outer wall of the diverter ring (4); The thickness of the inner wall of the diverter ring (4) located in the inner wall measurement area is greater than the thickness of the inner wall of the remaining parts of the diverter ring (4).

5. The intermediate casing test lead structure for aircraft engine fan testing according to claim 1, characterized in that: The outer wall measurement areas on the diverter ring (4) and their corresponding outer wall measurement covers (5) and outer wall measurement sensors (6) are distributed in multiple locations; The inner wall measurement areas on the diverter ring (4) and their corresponding inner wall measurement cover plates (7) and inner wall measurement sensors (8) are distributed in multiple locations.

6. The intermediate casing test lead structure for aircraft engine fan testing according to claim 1, characterized in that: The outer wall of the diverter ring (4) is provided with a plurality of assembly areas, and the outer wall located in the assembly area is provided with assembly installation grooves; The intermediate casing test lead structure for aircraft engine fan testing further includes: A plurality of assembly cover plates (9) are connected in each assembly installation groove, the front end is positioned with the front end of the assembly installation groove by a stop, the rear end has an inward folding edge, the inward folding edge is connected to the rear edge of the diverter ring (4) located in the assembly area by bolts, and spring washers are padded on the bolts.

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