Aeroengine test lead structure on an intermediate gearbox

Abstract

The application relates to a lead wire structure for testing an aero-engine on an intermediate casing, comprising an outer casing with an outer casing opening, an inner casing arranged in the outer casing and provided with an inner casing opening, a plurality of supporting plates arranged between the outer casing and the inner casing in a circumferential direction, one of the supporting plates being a cavity supporting plate, the cavity supporting plate being internally connected with the outer casing opening and the inner casing opening, a lead wire tube arranged in the cavity supporting plate, a sealing pressing plate arranged on the inner side of the inner casing and provided with a lead wire hole and an annular switching protrusion, the annular switching protrusion surrounding the lead wire hole and extending into the cavity supporting plate from the inner casing opening and being connected with one end of the lead wire tube, a lead-out tube with one end extending into the cavity supporting plate from the outer casing opening and being connected with the other end of the lead wire tube, a grommet sleeved on the outer periphery of the lead-out tube, and a nut threadedly connected on the lead-out tube, the nut being used for pressing the grommet against the outer side of the outer casing and making the sealing pressing plate abut against the inner side of the inner casing.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engine test lead structure design, and particularly relates to an aero-engine test lead structure on an intermediate casing. BACKGROUND

[0002] One of the performance optimization measures of an aero-engine is compressor component performance optimization, and an important item in the compressor component performance optimization is improvement of a rotor blade profile. After the improvement of the compressor rotor blade profile, dynamic stress measurement needs to be performed to master the dynamic strength reserve of the rotor blade after the profile improvement, so as to ensure safe control of the aero-engine.

[0003] For the dynamic stress measurement of the rotor blade after the profile improvement, currently, a dynamic stress patch is pasted on the rotor blade, the lead of the dynamic stress patch is led to a telemetry equipment lead wire arranged in a support point on the front side of the intermediate casing, after conversion by the telemetry equipment, the test lead is led out to the outside through an opening on the inner casing of the intermediate casing, a cavity of a support plate and an opening on the outer casing, and is connected with a test equipment to perform test data collection.

[0004] There is oil in the inner casing of the intermediate casing. In the current rotor blade dynamic stress measurement lead structure, in order to avoid the oil in the inner casing from entering the cavity of the support plate, the opening on the inner casing needs to be plugged. Since the inner casing is a thin-walled structure, it is not easy to plug. For this reason, currently, after the lead is led out from the cavity of the support plate, the cavity of the support plate is filled with sealing glue to achieve plugging of the opening on the inner casing. This technical solution is difficult to clean the sealing glue in the cavity of the support plate after the test is completed, and the lead is removed. When other test leads are needed, other support plates need to be modified. In the case that other support plates are occupied by functions such as air introduction, oil filling and oil return, it is difficult to perform tests.

[0005] The present application is proposed in view of the existence of the above technical defects. SUMMARY

[0006] The purpose of the present application is to provide an aero-engine test lead structure on an intermediate casing to overcome or alleviate at least one aspect of the known technical defects.

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

[0008] An aero-engine test lead structure on an intermediate casing comprises:

[0009] An outer casing having an outer casing opening thereon;

[0010] An inner casing arranged in the outer casing and having an inner casing opening thereon;

[0011] A plurality of support plates are circumferentially supported between the outer casing and the inner casing, one of which is a cavity support plate, the cavity support plate being internally connected to the outer casing opening and the inner casing opening;

[0012] A lead tube is arranged inside the cavity support plate;

[0013] A sealing pressure plate is arranged inside the inner casing and has a lead hole and an annular adapter protrusion thereon, the annular adapter protrusion surrounds the lead hole and extends into the cavity support plate from the inner casing opening and is connected to one end of the lead tube;

[0014] A lead-out tube is arranged to extend into the cavity support plate from the outer casing opening and is connected to the other end of the lead tube;

[0015] A grommet is arranged around the outer periphery of the lead-out tube;

[0016] A nut is threadedly connected to the lead-out tube to press the grommet against the outer side of the outer casing and to press the sealing pressure plate against the inner side of the inner casing;

[0017] The lead wire is led out through the inner casing opening, the lead hole, the annular adapter protrusion, the lead tube, the lead-out tube, and the outer casing opening, and sealing glue is injected into the lead-out tube.

[0018] According to at least one embodiment of the present application, in the lead wire structure on the intermediate casing of the aero-engine test, the two ends of the lead tube are connected by a lock seam welding between the annular adapter protrusion on the sealing pressure plate and the end of the lead-out tube extending into the cavity support plate.

[0019] According to at least one embodiment of the present application, in the lead wire structure on the intermediate casing of the aero-engine test, the threaded outer diameter of the lead-out tube is smaller than the maximum thickness L of the cavity support plate.

[0020] According to at least one embodiment of the present application, in the lead wire structure on the intermediate casing of the aero-engine test, the lead-out tube is internally provided with a thread, which is a stepped structure with a large hole facing outward.

[0021] According to at least one embodiment of the present application, in the lead wire structure on the intermediate casing of the aero-engine test, the outer diameter of the grommet is greater than the maximum thickness L of the cavity support plate.

[0022] According to at least one embodiment of the present application, in the lead wire structure on the intermediate casing of the aero-engine test, the nut is a self-locking nut.

[0023] According to at least one embodiment of the present application, in the lead wire structure on the intermediate casing of the aero-engine test, further comprising:

[0024] A sealing gasket is arranged around the outer periphery of the annular adapter protrusion and is arranged between the sealing pressure plate and the inner casing.

[0025] The present application has at least the following beneficial technical effects:

[0026] The present application provides an aero-engine test lead structure on an intermediate casing, which is simple and compact in overall structure, easy to disassemble and assemble, and uses a lead tube, a sealing pressure plate, a lead-out pipe and other components to build a lead channel between the outer casing, the inner casing and the support plate for leading out the lead, and after the lead is led out, a small amount of sealing glue can be injected into the lead-out pipe to achieve sealing, and after the measurement is completed, the sealing glue can be easily removed, the lead can be removed, and the nut can be unscrewed, and the sealing pressure plate, the lead tube and the lead-out pipe can be pulled out from the inner side of the inner casing to remove the lead. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 is a schematic diagram of an aero-engine test lead structure on an intermediate casing provided by the present application;

[0028] Figure 2 is a partial schematic diagram of Figure 1 ;

[0029] Figure 3 is another partial schematic diagram of Figure 1 ;

[0030] Figure 4 is a top view of the partial structure of Figure 1 ;

[0031] Among them:

[0032] 1-outer casing; 2-inner casing; 3-support plate; 4-lead tube; 5-sealing pressure plate; 6-lead-out pipe; 7-gasket ring; 8-nut; 9-sealing gasket.

[0033] In order to better illustrate the present application, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0034] 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 described in detail below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design.

[0035] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words indicating the orientation used in the description of the present application are only used to indicate the relative direction or positional relationship, and the relative positional relationship may also change accordingly when the absolute position of the described object changes. In the description of the present application, "including" indicates that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and other elements or objects are not excluded.

[0036] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the terms such as "mounting", "connection" 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; can be mechanical connection or electrical connection; can be directly connected or indirectly connected through intermediate medium, and those skilled in the art can understand the specific meaning of the terms in the present application according to the specific circumstances.

[0037] An aero-engine test lead structure on an intermediate casing, as shown in Figures 1-4 , comprising:

[0038] An outer casing 1 having an outer casing opening thereon;

[0039] An inner casing 2 arranged in the outer casing 1 and having an inner casing opening thereon;

[0040] A plurality of support plates 3 supported between the outer casing 1 and the inner casing 2 in a circumferential direction, one of which is a hollow support plate, the inside of which is communicated with the outer casing opening and the inner casing opening;

[0041] A lead tube 4 arranged in the inside of the hollow support plate;

[0042] A sealing pressure plate 5 arranged on the inner side of the inner casing 2 and having a lead hole and an annular adapter protrusion thereon, the annular adapter protrusion surrounding the lead hole and extending into the inside of the hollow support plate from the inner casing opening and connected with one end of the lead tube 4;

[0043] A lead-out tube 6 having one end extending into the inside of the hollow support plate from the outer casing opening and connected with the other end of the lead tube 4;

[0044] A grommet 7 sleeved on the outer periphery of the lead-out tube 6;

[0045] A nut 8 threadedly connected on the lead-out tube 6, pressing the grommet 7 against the outer side of the outer casing 1 and making the sealing pressure plate 5 abut against the inner side of the inner casing 2; the inner surface of the grommet 7 is adapted to the outer side of the outer casing 1, and the outer surface of the sealing pressure plate 5 is adapted to the profile of the inner side of the inner casing 2, so as to ensure the sealing effect;

[0046] The lead wire, specifically a rotor blade dynamic stress measurement lead wire, is led out through the inner casing opening, lead wire hole, annular adapter protrusion, lead wire tube 4, lead-out tube 6, outer casing opening, and is filled with sealant in the lead-out tube 6.

[0047] The lead wire structure for aero-engine testing on an intermediate casing disclosed in the above embodiment has a simple and compact overall structure, is convenient to disassemble and assemble, and uses the lead wire tube 4, seal pressing plate 5, and lead-out tube 6 to build a lead wire channel between the outer casing 1, inner casing 2, and support plate 3 for leading out the lead wire. After the lead wire is led out, a small amount of sealant can be filled in the lead-out tube 6 to achieve sealing. After the measurement is completed, the lead wire can be easily removed, or the nut 8 can be unscrewed, and the seal pressing plate 5, lead wire tube 4, and lead-out tube 6 can be pulled out from the inner side of the inner casing 1 as a whole to remove the lead wire.

[0048] In some optional embodiments of the lead wire structure for aero-engine testing on an intermediate casing, the lead wire tube 4 is connected by edge-welding between the annular adapter protrusion on the seal pressing plate 5 and the end of the lead-out tube 6 extending into the cavity support plate, and the connection is reliable.

[0049] In some optional embodiments of the lead wire structure for aero-engine testing on an intermediate casing, the outer diameter of the thread on the lead-out tube 6 is smaller than the maximum thickness L of the cavity support plate.

[0050] In some optional embodiments of the lead wire structure for aero-engine testing on an intermediate casing, the lead-out tube 6 is internally provided with a thread in a stepped structure with a large hole facing outward, so as to retain the sealant filled in the lead-out tube 6 and easily achieve sealing.

[0051] In some optional embodiments of the lead wire structure for aero-engine testing on an intermediate casing, the outer diameter of the grommet 7 is greater than the maximum thickness L of the cavity support plate, so as to be supported on the outer casing 1.

[0052] In some optional embodiments of the lead wire structure for aero-engine testing on an intermediate casing, the nut 8 is a self-locking nut.

[0053] In some optional embodiments of the lead wire structure for aero-engine testing on an intermediate casing, the lead wire structure further comprises:

[0054] The sealing gasket 9 is sleeved on the outer periphery of the annular adapter protrusion and is arranged between the seal pressing plate 5 and the inner casing 2 to ensure the sealing effect.

[0055] The various embodiments are described in the specification with progressive

[0056] So far, 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 these changes or replacements will all fall within the protection scope of the present application.

Claims

1. A lead wire structure for testing an aero-engine on an intermediate casing, characterized in that, include: Outer casing (1), which has an outer casing opening; The inner casing (2) is disposed inside the outer casing (1) and has an inner casing opening thereon; Multiple support plates (3) are circumferentially supported between the outer casing (1) and the inner casing (2). One of the support plates (3) is a cavity support plate, and the cavity support plate is connected to the opening of the outer casing and the opening of the inner casing. Lead tube (4) is installed inside the cavity support plate; The sealing pressure plate (5) is provided inside the inner casing (2), and has a lead wire hole and an annular transition protrusion. The annular transition protrusion surrounds the lead wire hole, extends from the opening of the inner casing into the cavity support plate, and is connected to one end of the lead wire tube (4). One end of the lead tube (6) extends from the opening of the outer casing into the cavity support plate and is connected to the other end of the lead tube (4); A gasket (7) is fitted around the outer circumference of the outlet pipe (6); Nut (8) is threaded onto lead-out pipe (6) to press washer (7) against the outside of outer casing (1) and to press sealing plate (5) against the inside of inner casing (2); The lead wire is led out through the inner casing opening, lead wire hole, annular transition protrusion, lead wire tube (4), lead wire tube (6), and outer casing opening, and sealant is injected into the lead wire tube (6); The lead-out tube (6) has internal threads and a stepped structure, with the large hole facing outwards.

2. The lead wire structure for testing aero-engines on the intermediate casing according to claim 1, characterized in that, The two ends of the lead tube (4) are connected to the annular transition protrusion on the sealing pressure plate (5) and the end of the lead tube (6) that extends into the cavity support plate by welding lock edge welding.

3. The lead wire structure for testing aero-engines on the intermediate casing according to claim 1, characterized in that, The outer diameter of the thread on the lead-out pipe (6) is smaller than the maximum thickness L of the cavity support plate.

4. The lead wire structure for testing aero-engines on the intermediate casing according to claim 1, characterized in that, The outer diameter of the gasket (7) is greater than the maximum thickness L of the cavity support plate.

5. The lead wire structure for testing aero-engines on an intermediate casing according to claim 1, characterized in that, Nut (8) is a self-locking nut.

6. The lead wire structure for testing aero-engines on an intermediate casing according to claim 1, characterized in that, Also includes: The sealing gasket (9) is fitted on the outer periphery of the annular transition protrusion and is placed between the sealing pressure plate (5) and the inner casing (2).

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