Turbine support flow test apparatus

Abstract

The application discloses a device for testing turbine support flow, which comprises a pipe joint, a nozzle, a plugging screw and a hose. The pipe joint is an N-way pipe, comprising a plurality of interfaces. An annular sealing groove is formed on the end face or inner wall of the interface. An inner thread is formed on the inner wall of part of the interfaces. An oil inlet interface and an oil supply nozzle hole are arranged on the nozzle. The part of the nozzle with the oil supply nozzle hole is inserted into the inner cavity of the pipe joint through the interface, so that the oil supply nozzle hole is communicated with at least part of the interfaces. The oil inlet interface of the nozzle is located outside the pipe joint. The plugging screw is detachably connected with the interface through the inner thread. One end of the hose is detachably connected with the interface, and the other end of the hose is communicated with an oil metering container. The device is simple and practical, has good sealing performance, and can meet the test of turbine support flow of multiple models.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of metrological testing, in particular, a device for turbine support flow testing. BACKGROUND

[0002] In the process of turbine support flow testing of an aero-engine, the existing turbine support flow pipe joint has poor sealing, oil leakage, and large error in measured flow value, which leads to the fact that the existing turbine support flow pipe joint cannot meet the assembly technical requirements. On the other hand, some oil supply nozzles used in turbine support flow testing are designed with two oil supply nozzle holes, while the existing turbine support flow pipe joint can only test one oil supply nozzle hole.

[0003] Based on the above reasons, a universal, sealed and accurate pipe joint device is needed to meet the technical requirements. SUMMARY

[0004] The present application aims to provide a device for turbine support flow testing, in particular, a simple and practical device with good sealing and capable of meeting the testing of turbine support flow of multiple models (with different numbers of oil supply nozzle holes).

[0005] The technical solution of the present application is as follows:

[0006] The device for turbine support flow testing comprises,

[0007] The pipe joint is an N-way pipe, comprising a first interface, a second interface,..., and an Nth interface, N being a natural number greater than two, wherein the end face of the second interface,..., and the Nth interface is provided with an annular sealing groove, and the inner wall of the second interface,..., and the Nth interface is provided with an internal thread;

[0008] The nozzle is provided with an oil inlet interface and an oil supply nozzle hole, the number of the oil supply nozzle hole is less than or equal to N, and the part of the nozzle with the oil supply nozzle hole is inserted into the inner cavity of the pipe joint through the first interface, so that the oil supply nozzle hole is in communication with at least one of the second interface,..., and the Nth interface, and the oil inlet interface of the nozzle is located outside the pipe joint;

[0009] The plugging screw is detachably connected with the second interface,..., and the Nth interface through the internal thread of the second interface,..., and the Nth interface;

[0010] The hose is detachably connected with the second interface,..., and the Nth interface at one end, and is in communication with the oil metering container at the other end.

[0011] Further, the pipe joint is further provided with a threaded hole for fastening the nozzle, the threaded hole is in communication with the inner cavity of the pipe joint, and the plugging screw is detachably connected in the threaded hole.

[0012] Further, a sealing ring is arranged in the annular sealing groove of the second interface and the Nth interface.

[0013] Further, the threaded hole is located on a planar surface of the pipe joint, and an annular sealing groove is formed on the hole end face of the threaded hole, and a sealing ring is arranged in the annular sealing groove.

[0014] Alternatively, the second interface and the Nth interface extend outward from the surface of the pipe joint through branch pipes.

[0015] Further, the axes of the branch pipes are not parallel.

[0016] Alternatively,

[0017] The inner wall of the first interface is provided with a first annular sealing groove;

[0018] The nozzle comprises an oil supply nozzle section inserted into the inner cavity of the pipe joint in a straight line, and an oil inlet interface section in a curved shape, and a sealing ring is arranged between the outer surface of the oil supply nozzle section and the first annular sealing groove of the inner wall of the first interface.

[0019] Compared with the prior art, the present application has the following characteristics:

[0020] (1) In the present application, sealing structures composed of sealing rings and annular sealing grooves are used between the pipe interface and the nozzle, the plugging screw and the hose, the sealing effect is good, and there is no oil leakage during the measurement process;

[0021] (2) The present application is easy to disassemble, either through threaded connection or direct insertion, which is convenient for test operation;

[0022] (3) The present application has good universality and interchangeability, the number of interfaces and the positional relationship between the interfaces are designed according to the number of the largest oil supply nozzle holes on the nozzle and the positional relationship between the oil supply nozzle holes, so that one pipe joint can be used for different model flow test requirements. When the number of oil supply nozzle holes is less than the number of interfaces, the redundant interfaces are plugged and sealed by plugging screws;

[0023] (4) The present application can be used for testing the flow of various turbine supports. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 is a schematic view of a pipe joint;

[0025] Figure 2 is a schematic view of a nozzle;

[0026] Figure 3 is an enlarged view of the threaded hole and the first interface on the pipe joint;

[0027] Figure 4 is a schematic view of a plugging screw;

[0028] Figure 5 A schematic diagram of the second and third interfaces on the pipe fitting, extended by a branch pipe;

[0029] Figure 6 This is a schematic diagram showing the connection between the pipe fitting and the nozzle through the first interface.

[0030] Figure 7 This is a cross-sectional schematic diagram of the pipe fitting;

[0031] Figure 8 , Figure 9 , Figure 10 These are views of the pipe fitting from different angles;

[0032] Figure 11 , Figure 12 , Figure 13 These are views of the nozzle at different angles;

[0033] In the diagram, 1 is the pipe fitting; 2 is the nozzle; 3 is the sealing screw; 4 is the oil supply port nozzle; 5 is the annular sealing groove; and 6 is the sealing ring. Detailed Implementation

[0034] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0035] like Figures 1-13 As shown, in this embodiment, the turbine support flow test device includes a pipe joint 1, a nozzle 2, a sealing screw 3, and a sealing ring 6.

[0036] Specifically, the pipe connector 1 is constructed as a three-way pipe. Depending on the location of the oil supply nozzle hole 4 for different models, a second and third interface, serving as the oil outlet, are positioned on the pipe connector 1. The second and third interfaces extend outwards from the surface of the pipe connector 1 via branch pipes. An annular sealing groove 5 is machined on the end face of the branch pipe, and internal threads are machined on the inner wall of the branch pipe end. The first interface on the pipe connector 1 is located at one end of the inner cavity of the pipe connector 1, and an annular sealing groove 5 is machined on the inner wall near the end. Along the axial direction of the inner cavity and on the outer surface of the pipe connector 1, there is a plane with two threaded holes. These threaded holes communicate with the inner cavity, and an annular sealing groove 5 is machined on the plane of the threaded hole opening. The nozzle 2 has a structure with a straight section and a curved section. The straight section has an oil supply nozzle 4.

[0037] Before testing, the straight part of the nozzle 2 with the oil supply hole nozzle 4 is inserted into the inner cavity of the pipe joint 1 from the first interface of the pipe joint 1, and the sealing ring 6 is installed between the straight part of the nozzle 2 and the annular sealing groove 5 at the first interface. Then, the sealing ring 6 is installed in the annular sealing groove 5 of the threaded hole orifice of the pipe joint 1, and then the plug screw 3 is screwed into the two threaded holes on the surface plane of the pipe joint 2 until the straight part of the nozzle 2 is compressed. The second interface and the third interface are connected to the standard hose as oil outlets. The angle between the second interface (with a branch pipe) and the third interface (with a branch pipe) as oil outlets is the same as the angle of the two oil supply nozzle holes 4 on the nozzle 2, and the sealing ring 6 is also installed in the annular sealing groove 5 at the end face of the second interface and the third interface. The second interface and the third interface as oil outlets are connected to the 1000ml measuring cup through the standard hose.

[0038] When the turbine support has only one oil supply nozzle hole 4, the unused oil outlet (second interface or third interface) is equipped with a sealing ring 6 and a plug screw 3. The annular sealing groove 5 is provided between the pipe joint 1 and the plug screw 3, and the plug screw 3 is sealed by the end face. After the pipe joint 1 is installed, the plug screw 3 is tightened with a wrench. The entire device has one pipe joint 1, three plug screws 3, three end face sealing rings 6, one inner diameter sealing ring 6 at the first interface, and two 1-meter-long standard 7-inch hoses.

[0039] The turbine support flow testing device of the present application selects appropriate standard sealing rings 6 to be installed in the annular sealing grooves 5 at the connection, forming four end face sealing structures and one inner diameter sealing structure; the plug screw 3 has three parts, which can block the second interface or the third interface, and can also compress the nozzle 2 from the threaded hole; the second interface and the third interface are made into oil outlets that can be connected to standard 7-inch hoses. The threaded holes for compressing the nozzle 2 of the second interface, the third interface, and the plug screw 3 are all M8, and the threads of the plug screw 3 are also M8.

[0040] The pipe joint 1 of the present application has good universality and interchangeability. When other models of turbine supports have only one oil supply nozzle hole 4, the pipe joint 1 of the present application can also be used. By installing a sealing ring 6 with a plug screw 3, one of the interfaces (oil outlets) is blocked, and the other interface (oil outlet) is connected to a standard hose for testing. The present application is provided with an annular sealing groove 5 and a sealing ring 6 at the connection, which prevents oil leakage and ensures the accuracy of the measured value to meet the technical requirements of turbine support flow testing.

[0041] The description of the application herein is not intended to be detailed and is well known to those skilled in the art. Although the above describes the specific embodiments of the application in order to facilitate the understanding of the application for those skilled in the art, it should be clear that the application is not limited to the scope of the specific embodiments, and for those skilled in the art, it is obvious that various changes are within the spirit and scope of the application defined and determined by the appended claims, and all the applications using the concept of the application are within the scope of protection.

Claims

1. A turbine support flow test apparatus, characterised in that: The utility model relates to a pipe joint (1) and a nozzle (2) and a sealing screw (3) and a hose, and the pipe joint (1) is an N-way pipe joint, comprising a first interface, a second interface and an Nth interface, wherein the end face of the second interface and the Nth interface is provided with an annular sealing groove (5), and the inner wall of the second interface and the Nth interface is provided with internal threads. The nozzle (2) is provided with an oil inlet interface and an oil supply nozzle hole (4), the number of the oil supply nozzle hole (4) is less than or equal to N, and the part of the nozzle (2) provided with the oil supply nozzle hole (4) is inserted into the inner cavity of the pipe joint (1) through the first interface so that the oil supply nozzle hole (4) is communicated with at least one of the second interface and the Nth interface, and the oil inlet interface of the nozzle (2) is located outside the pipe joint (1). The sealing screw (3) is detachably connected with the second interface and the Nth interface through the internal threads of the second interface and the Nth interface. One end of the hose is detachably connected with the second interface and the Nth interface, and the other end is communicated with an oil metering container. The pipe joint (1) is further provided with a threaded hole for fastening the nozzle (2), the threaded hole is communicated with the inner cavity of the pipe joint (1), and the sealing screw (3) is detachably connected in the threaded hole. The second interface and the Nth interface are extended outward from the surface of the pipe joint (1) through branch pipes. The axes of the branch pipes are not parallel. The inner wall of the first interface is provided with an annular sealing groove (5). The nozzle (2) comprises an oil supply nozzle section inserted into the inner cavity of the pipe joint (1) in a straight line and an oil inlet interface section in a curved shape, and a sealing ring (6) is arranged between the outer surface of the oil supply nozzle section and the annular sealing groove (5) of the inner wall of the first interface. The threaded hole is located on a planar surface of the pipe joint (1), and the hole opening end face of the threaded hole is provided with an annular sealing groove (5), and a sealing ring (6) is arranged in the annular sealing groove (5).

2. The turbo support flow testing apparatus of claim 1, wherein: The annular sealing groove (5) of the second interface and the Nth interface is provided with a sealing ring (6).

3. The turbine support flow test apparatus of claim 1, wherein: ​

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