Aircraft engine ground test run deflation tool

Abstract

The utility model discloses an aero-engine ground test run deflation tool which is characterized in that the aero-engine ground test run deflation tool comprises a connecting joint, a block body and an ejector rod, a through hole is formed in the block body, the connecting joint penetrates through the through hole, the connecting joint is provided with an inner hole in the axial direction, the ejector rod penetrates through the inner hole of the connecting joint, an oil drainage hole is connected to the lower portion of the through hole, and the oil drainage hole is connected to the lower portion of the block body. A through hole communicated with the through hole and an inner hole of the connecting joint is formed in the section, located in the through hole, of the connecting joint. The engine can be deflated at any temperature, and whether air exists in the discharged medium or not can be checked; connecting the tool with the engine until the disassembly of the tool is completed, wherein the time is not longer than 3 minutes; the transparent PU hose is adopted as the oil drainage hose and can resist oil and the temperature of 120 DEG C, and the state of a medium in the hose can be checked.

Description

Technical Field

[0001] The utility model relates to a ground handling equipment, in particular to an airworthiness test air bleeding tool for an aeroengine on the ground. Background Art

[0002] At present, the parking fuel draining device of an aircraft engine fuel distributor is a one-way valve structure. The existing air bleeding tool design has a protrusion in front of a connecting joint of M8×1.25. When the connecting joint is screwed into the fuel draining device, while screwing the thread, the protruding part also moves towards the pipeline. When the protrusion contacts the one-way valve in the pipeline, the oil in the one-way valve starts to spray outwards, and at the same time, the internal air is discharged. Since the oil starts to be discharged during the process of screwing the thread, the oil splashes everywhere. When the oil temperature is too high, it may scald the operator, or the oil splashes onto the operator's body. Therefore, the current air bleeding and fuel draining operation needs to wait until the engine temperature drops to normal temperature before draining fuel. It is estimated that it takes 30 minutes for the engine to cool down to normal temperature. At the same time, there is no way to collect the fuel during the original fuel draining process, and it will splash everywhere. Content of the Utility Model

[0003] The purpose of the utility model is to provide an airworthiness test air bleeding tool for an aeroengine on the ground, so as to solve the disadvantage of inconvenient use of the existing airworthiness test air bleeding tool for an aeroengine on the ground.

[0004] The utility model is realized by adopting the following technical scheme: an airworthiness test air bleeding tool for an aeroengine on the ground, characterized in that it comprises a connecting joint, a block body, and a ejector rod. A through hole is arranged in the block body, and the connecting joint passes through the through hole. The connecting joint is provided with an inner hole along the axial direction, the ejector rod passes through the inner hole of the connecting joint, a fuel draining hole is connected below the through hole, and a through hole communicating the through hole with the inner hole of the connecting joint is arranged on a section of the connecting joint located in the through hole.

[0005] Further, sealing rings are arranged at the contact positions between the connecting joint and the two end faces of the through hole.

[0006] Further, a pipe joint is also arranged below the block body, and a transparent PU hose is connected through the pipe joint. A fuel draining hole communicating with the through hole is arranged in the pipe joint.

[0007] Further, one end of the connecting joint is provided with an external thread and is connected to the engine through the external thread, and the other end is fixedly connected with a nut.

[0008] Further, the nut is provided with an inner hole coaxial with the connecting joint and communicating with the inner hole of the connecting joint.

[0009] Further, the ejector rod passes through the inner holes of the connecting joint and the nut at the same time.

[0010] Further, a threaded section is provided on the ejector rod, an internal thread is provided in the inner hole of the nut, and the threaded section is engaged with the internal thread in the inner hole of the nut.

[0011] The beneficial effects of an air bleeding tooling for ground test run of an aeroengine according to the present utility model include:

[0012] 1. The engine can bleed air at any temperature, and it can be checked whether there is air in the discharged medium;

[0013] 2. The tooling is connected to the engine until the tooling is disassembled, which takes no more than 3 minutes;

[0014] 3. A transparent PU hose is used as the oil discharge hose, which can resist oil and a temperature of 120 °C, and the state of the medium in the hose can also be checked. Description of the Drawings

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. The following drawings are only some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on the structures shown in these drawings.

[0016] Figure 1 It is a schematic diagram of an air bleeding tooling for ground test run of an aeroengine;

[0017] Figure 2 It is a schematic diagram of a block;

[0018] Figure 3 It is a schematic diagram of a connecting joint;

[0019] Figure 4 It is a schematic diagram of an ejector rod;

[0020] In the figure, 1 - connecting joint; 2 - block; 3 - pipe joint; 4 - nut; 5 - ejector rod; 6 - through hole; 7 - threaded section. Detailed Embodiments

[0021] To make the objectives, technical solutions and advantages of the embodiments of the present utility model clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present utility model in conjunction with the drawings in the embodiments of the present utility model. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model. Usually, the components of the embodiments of the present utility model described and illustrated in the drawings here can be arranged and designed in various different configurations.

[0022] Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed present invention, but merely represents selected embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without creative efforts fall within the scope of protection of the present invention.

[0023] As Figure 1 shown, an air bleeding tooling for ground test run of an aeroengine includes a connection joint 1, a block 2, and a push rod 5. A through hole 6 is provided in the block 2, and the connection joint 1 passes through the through hole 6. Sealing rings are provided at the contact surfaces between the connection joint 1 and the two end faces of the through hole 6. The connection joint 1 is provided with an inner hole along the axial direction, and the push rod 5 passes through the inner hole of the connection joint 1. One end of the connection joint 1 is provided with an external thread and is connected to the engine through the external thread, while the other end is fixedly connected with a nut 4. During use, the connection joint 1 is screwed in by rotating the nut 4. The nut 4 is provided with an inner hole coaxial with the connection joint 1. A pipe joint 3 is provided below the block 2, and a transparent PU hose is connected through the pipe joint 3 to collect the discharged oil. An inner hole communicating with the through hole 6 is provided in the pipe joint 3. A through hole perpendicular to the inner hole of the connection joint 1 is provided in the part of the connection joint 1 inserted into the through hole 6, so that the oil can enter the block 2 through the connection joint 1 and then be discharged from the pipe joint 3.

[0024] A threaded section 7 is provided on the push rod 5, and an internal thread matching the threaded section 7 is provided in the inner hole of the nut 4. A sealing ring is also provided between the push rod 5 and the nut 4. During use, first connect the connection joint 1 to the engine, and then rotate the push rod 5 to make the push rod 5 advance to push open the one-way valve. When the oil flows out, stop rotating the push rod 5 until there are no bubbles in the transparent PU hose.

[0025] In the above embodiments, the basic principles, main features, and advantages of the present invention are described. Those skilled in the art of this industry should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification only illustrates the principle of the present invention. Without departing from the spirit and scope of the present invention, any changes and modifications made by those skilled in the art that do not depart from the spirit and scope of the present invention should fall within the scope of protection of the appended claims of the present invention.

Claims

1. An aircraft engine ground test and venting tool, characterized in that: The invention comprises a connecting joint (1), a block (2), and a push rod (5); the block (2) is provided with a through hole (6), the connecting joint (1) passes through the through hole (6), the connecting joint (1) is provided with an inner hole along the axial direction, the push rod (5) passes through the inner hole of the connecting joint (1), an oil drain hole is connected below the through hole (6), and a through hole connecting the through hole (6) and the inner hole of the connecting joint (1) is provided on a section of the connecting joint (1) located inside the through hole (6).

2. The aircraft engine ground test and venting tool according to claim 1, characterized in that: Sealing rings are provided at the contact points between the two end surfaces of the connecting joint (1) and the through hole (6).

3. The aircraft engine ground test and venting tool according to claim 1, characterized in that: A pipe joint (3) is also provided below the block (2), and a transparent PU hose is connected via the pipe joint (3). An oil drain hole communicating with the through hole (6) is provided in the pipe joint (3).

4. The aircraft engine ground test and venting tool according to claim 1, characterized in that: One end of the connecting joint (1) is provided with an external thread and is connected to the engine via the external thread, while the other end is fixedly connected with a nut (4).

5. The aircraft engine ground test and venting tool according to claim 4, characterized in that: The nut (4) is provided with an inner hole coaxial with the connecting joint (1), and is communicated with the inner hole of the connecting joint (1).

6. The aircraft engine ground test and venting tool according to claim 4, characterized in that: The push rod (5) passes through the inner holes of the connecting joint (1) and the nut (4) at the same time.

7. The aircraft engine ground test and venting tool according to claim 6, characterized in that: The push rod (5) is provided with a threaded section (7), the inner hole of the nut (4) is provided with an internal thread, and the threaded section (7) cooperates with the internal thread in the inner hole of the nut (4).

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