Fixture for pressure airtightness test of rectification bearing casing and use method thereof

Abstract

The invention discloses a pressure air tightness test fixture for a rectification bearing casing and a use method, the test fixture comprises a bottom plate and a cover plate connected to the upper space of the bottom plate through a B-level equal-length double-end stud, the bottom plate and the cover plate are respectively provided with a first sealing ring and a second sealing ring in a matched manner, and the cover plate is provided with a plurality of screw holes; a first pressing plate and a second pressing plate are fixed between the bottom plate and the cover plate through an arch-shaped frame and a C-shaped hexagonal head compression screw, a first sealing gasket and a second sealing gasket are arranged on the first pressing plate and the second pressing plate in an attached mode respectively, and an adapter nozzle is connected to the first pressing plate. The fixture realizes the pressure airtightness test of the whole part welding seam, solves the prominent problem of low efficiency of single support plate welding seam one-by-one test, and improves the pressure airtightness test quality and the part processing efficiency.

Description

Technical Field

[0001] The invention belongs to the technical field of pressure and air tightness test fixtures, and in particular relates to a pressure and air tightness test fixture for a fairing support casing and a use method thereof. Background Art

[0002] Reference Figure 4 and Figure 5 The fairing support casing is installed in the turbine support part of the aircraft engine. It is an important core component of the aircraft engine turbine support. Lubricating oil and compressed cold air flow in the cavity of the fairing support casing. At the same time, it is one of the load-bearing points of the static parts of the aircraft engine, and it bears large mechanical loads and impacts. The fairing support casing is welded by the inner casing and the support plate to form a large number of cavities, and the weld strength needs to be quickly tested for pressure and air tightness.

[0003] The Chinese invention patent with publication number CN112345170B discloses an air tightness detection fixture and detection method for aircraft engine support casings, which divides multiple cavities into two steps for air tightness detection, namely, the S cavity and the support plate inner cavity are detected separately. However, the separate detection has the problem of complicated operation process. Summary of the invention

[0004] In order to solve the above problems, the present invention aims to provide a pressure air tightness test fixture for a fairing support casing and a method for using the same.

[0005] In order to achieve the above-mentioned object, the present invention adopts the following technical scheme: a pressure airtightness test fixture for a fairing support casing, comprising a bottom plate, a cover plate arranged in the upper space of the bottom plate connected by B-grade equal-length studs, a first sealing ring and a second sealing ring are respectively provided on the bottom plate and the cover plate, and a plurality of screw holes are opened on the cover plate;

[0006] A first pressing plate and a second pressing plate are fixed between the bottom plate and the cover plate by means of a bow frame and a C-shaped hexagonal clamping screw, a first sealing gasket and a second sealing gasket are respectively fitted on the first pressing plate and the second pressing plate, and a transfer nozzle is connected to the first pressing plate.

[0007] Preferably, a coaxial stop is provided on the upper end surface of the base plate, and a threaded hole is also provided for connection with a Class B equal-length stud.

[0008] Preferably, the screw holes provided on the cover plate are matched with the screws, the screws are mounted on the cover plate, and connected with the threaded holes on the rear wall plate of the rectifier support casing.

[0009] Preferably, the first sealing ring is assembled on the base plate to ensure that the base plate is tightly attached to the front wall plate of the fairing support casing. The second sealing ring is arranged on the side end of the cover plate and assembled on the end face of the oil support plate of the fairing support casing, so that the first pressure plate fits tightly to the end face of the oil support plate.

[0010] Preferably, two surfaces of the first pressure plate are respectively connected to the adapter nozzle and the second sealing ring, and are fitted with the end surface of the support plate by screwing the C-shaped hexagonal head clamping screws on the bow frame.

[0011] Preferably, the gasket is assembled between the adapter nozzle and the first pressure plate.

[0012] Preferably, the adapter nozzle is mounted on the oil support plate of the rectifying support casing, the exhaust end is connected to the first pressure plate, and the intake end is connected to the high-pressure gas.

[0013] Preferably, the material of the bottom plate, cover plate, screws, first pressure plate, bow frame, adapter nozzle and second pressure plate is 1Cr18Ni9Ti; the material of the first sealing ring, second sealing ring, first sealing gasket and second sealing gasket is polytetrafluoroethylene; the material of the gasket is T2.

[0014] A method for using a pressure air tightness test fixture for a rectifier support casing, characterized in that it comprises the following steps:

[0015] Step 1: Loosen the C-type hexagonal head compression screw and the hexagonal nut on the B-grade equal-length stud;

[0016] Step 2: Install the fairing support casing into the test fixture, ensure that the inner casing stop of the fairing support casing fits with the bottom plate stop to ensure coaxiality, install the cover plate, tighten the screws, and ensure that it fits tightly with the threaded hole of the rear wall plate of the fairing support casing;

[0017] Step 3: Connect the adapter nozzle to high-pressure air and observe the sealing of the weld.

[0018] Preferably, the test sealing of the support plate end face is ensured by tightening the C-type hexagonal head compression screw on the bow frame; the test sealing of the front wall plate of the fairing support casing is ensured by tightening the hexagonal nut on the B-grade equal-length double-headed stud; the sealing of the threaded holes on the rear wall plate of the fairing support casing is ensured by tightening the screws; an air intake system is formed by an adapter nozzle, a first pressure plate, and a first sealing gasket to ensure high-pressure air to enter the sealed cavity of the fairing support casing and realize underwater pressure airtightness inspection of the weld.

[0019] Compared with the prior art, the present invention has the following advantages:

[0020] 1. The operation is simple. You only need to install the base plate, cover plate, first pressure plate, second pressure plate, tighten the screws, C-type hexagonal head clamping screws, and hexagonal nuts on Class B equal-length studs. Pass high-pressure gas through the adapter nozzle to check the strength of the seven support plates and the inner casing welds of the rectifier support casing as a whole.

[0021] 2. High detection efficiency. The use of the rectifier support casing pressure air tightness test fixture can simultaneously detect the welds on the support plate and the inner casing, and process them at the same time, avoiding the inefficiency of checking multiple support plates one by one, and significantly improving the parts processing efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the specific embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 It is a schematic diagram of a pressure air tightness test fixture for a fairing support casing of the present invention;

[0024] Figure 2 for Figure 1 AA section view;

[0025] Figure 3 for Figure 1 BB cross-section diagram;

[0026] Figure 4 The rectifier support casing of the present invention is shown in FIG. Figure 1 ;

[0027] Figure 5 The rectifier support casing of the present invention is shown in FIG. Figure 2 ;

[0028] In the figure, 1-base plate, 2-first sealing ring, 3-cover plate, 4-screw, 5-second sealing ring, 6-first sealing gasket, 7-first pressure plate, 8-bow frame, 9-gasket, 10-adapter nozzle, 11-second sealing gasket, 12-second pressure plate, 13-C-type hexagon head clamping screw, 14-B-grade equal-length stud bolt, 15-hexagon nut, 16-hexagon flat nut. DETAILED DESCRIPTION

[0029] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0030] Reference Figure 1-Figure 3 The pressure air tightness test fixture of the fairing support casing of the present invention is mainly composed of a base plate 1, a first sealing ring 2, a cover plate 3, a screw 4, a second sealing ring 5, a first sealing gasket 6, a first pressure plate 7, a bow frame 8, a gasket 9, an adapter nozzle 10, a second sealing gasket 11, a second pressure plate 12, a C-type hexagonal head clamping screw 13, a B-level equal-length stud 14, a hexagonal nut 15, and a hexagonal flat nut 16.

[0031] A bottom plate 1, wherein a first sealing ring 2 and a coaxial stopper are provided on the upper end surface of the bottom plate 1, and the bottom plate 1 is fastened to the cover plate 3 by means of a Class B equal-length stud 14;

[0032] A first sealing ring 2, which is assembled on the bottom plate 1 to ensure that the bottom plate 1 is tightly fitted with the front wall of the component;

[0033] The cover plate 3 has screw holes and is connected to the bottom plate via Class B studs of equal length;

[0034] Screws 4 are mounted on the cover plate 3 and are connected and sealed with threaded holes on the rear wall plate of the rectifier support casing;

[0035] A second sealing ring 5, which is mounted on the end surface of the oil support plate of the rectifier support casing to ensure tightness between the first pressure plate 7 and the end surface of the oil support plate;

[0036] A first sealing gasket 6, which is mounted on the end surface of the oil support plate of the rectifier support casing to ensure that the first pressure plate 7 is tightly fitted with the end surface of the support plate;

[0037] The first pressing plate 7 is mounted on the end face of the oil support plate of the rectifier support casing, and its two sides are respectively connected to the adapter nozzle 10 and the second sealing ring 5, and the first pressing plate 7 is ensured to be closely fitted with the end face of the support plate by screwing the C-shaped hexagonal head clamping screw 13 on the bow frame 8;

[0038] The arch frame 8 is a force-bearing frame to ensure that the end faces of the seven support plates are closely attached to the first pressing plate 7 and the second pressing plate 12;

[0039] A gasket 9, wherein the gasket 9 is assembled between the adapter nozzle 10 and the first pressing plate 7 to ensure the tightness of the adapter nozzle 10;

[0040] The adapter nozzle 10 is mounted on the oil support plate of the rectifying support casing, the exhaust end is connected to the first pressure plate 7, and the intake end is connected to the high-pressure gas;

[0041] The second sealing gasket 11, the gasket 2 is assembled on the remaining 6 support plate end faces to ensure the tightness of the pressure plate and the support plate end faces;

[0042] A second pressing plate 12, which is assembled on the remaining 6 support plate end surfaces and fits tightly with the second sealing gasket 11;

[0043] A C-shaped hexagonal clamping screw 13, which is connected to the first clamping plate 7 and the second clamping plate 12 through the bow frame 8. Screwing the C-shaped hexagonal clamping screw 13 ensures that the second clamping plate 12, the first clamping plate 7 and the end surface of the support plate are tightly fitted;

[0044] Class B equal-length studs 14 are assembled between the base plate 1 and the cover plate 3. By screwing the hexagonal nuts thereon, the base plate 1 and the cover plate 3 are tightly connected, and also ensure a tight fit with the front wall plate of the fairing support casing to ensure sealing.

[0045] The base plate 1, the cover plate 3, the screws 13, the first pressure plate 7, the bow frame 8, the adapter nozzle 10 and the second pressure plate 12 are made of 1Cr18Ni9Ti, the first sealing ring 2, the second sealing ring 5, the first sealing gasket 6 and the second sealing gasket 11 are made of polytetrafluoroethylene, and the gasket 9 is made of T2.

[0046] The test sealing of the support plate end face is ensured by tightening the C-type hexagonal head clamping screw 13 on the bow frame 8; the test sealing of the front wall plate of the rectifier support casing is ensured by tightening the hexagonal nut on the B-level equal-length double-headed stud 14; the sealing of the threaded holes on the rear wall plate of the rectifier support casing is ensured by tightening seven screws; the air intake system is formed by the adapter nozzle 10, the first pressure plate 7, and the first sealing gasket 6 to ensure high-pressure air to enter the rectifier support casing sealing cavity and realize the underwater pressure airtightness inspection of the weld.

[0047] The pressure air tightness test fixture of the fairing support casing adopts the above-mentioned deformation control device and includes the following steps:

[0048] Step 1: Loosen the C-type hexagon head clamping screw 13 and the hexagon nut 15 and hexagon flat nut 16 on the B-grade equal-length stud 14;

[0049] Step 2: Install the fairing support casing into the test fixture, and ensure that the inner casing stop of the fairing support casing fits the stop of the bottom plate 1 to ensure coaxiality. Install the cover plate 3, tighten the seven screws, and ensure that the threaded holes of the rear wall of the fairing support are tightly fitted;

[0050] Step 3: Connect the adapter nozzle to high-pressure air and observe the sealing of the weld;

[0051] Step 4: Disassemble the fixture: loosen the screw 4, the C-type hexagonal head clamping screw 13, the hexagonal nut 15 and the hexagonal flat nut 16 on the B-grade equal-length stud, and take out the parts.

[0052] Design and manufacture a pressure and air tightness test fixture for the rectifier support casing to realize pressure and air tightness testing of the entire weld of the parts, solve the prominent problem of slow testing efficiency of each single plate weld, and improve the quality of pressure and air tightness testing and parts processing efficiency.

[0053] The above is a detailed introduction to a pressure air tightness test fixture and a method of use of a fairing support casing provided by the present invention. This article uses specific examples to illustrate the structure and working principle of the present invention. The description of the above embodiments is only used to help understand the method and core idea of ​​the present invention. It should be pointed out that for ordinary technicians in this technical field, without departing from the principle of the present invention, the present invention can also be improved and modified in a number of ways, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. A pressure air tightness test fixture for a fairing support casing, characterized in that: It comprises a base plate (1), a cover plate (3) arranged in the upper space of the base plate (1) connected by means of B-grade equal-length studs (14), a first sealing ring (2) and a second sealing ring (5) being respectively provided on the base plate (1) and the cover plate (3), and a plurality of screw holes being provided on the cover plate (3); A first pressing plate (7) and a second pressing plate (12) are fixed between the bottom plate (1) and the cover plate (3) via a bow frame (8) and a C-shaped hexagonal head clamping screw (13); a first sealing gasket (6) and a second sealing gasket (11) are respectively provided on the first pressing plate (7) and the second pressing plate (12); and a transfer nozzle (10) is connected to the first pressing plate (7).

2. The pressure and air tightness test fixture for the fairing support casing according to claim 1 is characterized in that: The upper end surface of the bottom plate (1) is provided with a coaxial stopper and a threaded hole for connection with a Class B equal-length stud (14).

3. The pressure and air tightness test fixture for the fairing support casing according to claim 1 is characterized in that: The screw holes provided on the cover plate (3) are matched with the screws (4), the screws (4) are assembled on the cover plate (3) and connected with the threaded holes on the rear wall plate of the rectifier support casing.

4. The pressure and air tightness test fixture for fairing support casing according to claim 1 is characterized in that: The first sealing ring (1) is mounted on the bottom plate (1) to ensure that the bottom plate (1) is tightly fitted to the front wall plate of the rectifier support casing. The second sealing ring (5) is arranged at the front end of the cover plate (3) and is mounted on the end surface of the oil support plate of the rectifier support casing, so that the first pressure plate (7) is tightly fitted to the end surface of the oil support plate.

5. The pressure and air tightness test fixture for fairing support casing according to claim 1 is characterized in that: The first pressing plate (7) is connected to the adapter nozzle (10) and the second sealing ring (5) on both sides respectively, and is fitted to the end surface of the support plate by screwing the C-shaped hexagonal head clamping screw (13) on the bow frame (8).

6. The pressure and air tightness test fixture for fairing support casing according to claim 1, characterized in that: The gasket (9) is assembled between the adapter nozzle (10) and the first pressing plate (7).

7. The pressure and air tightness test fixture for fairing support casing according to claim 1 is characterized in that: The adapter nozzle (10) is assembled at the oil support plate of the rectifying support casing, the exhaust end is connected to the first pressure plate (7), and the intake end is connected to the high-pressure gas.

8. The pressure and air tightness test fixture for fairing support casing according to claim 1 is characterized in that: The material of the bottom plate (1), the cover plate (3), the screw (4), the first pressing plate (7), the bow frame (8), the adapter nozzle (10) and the second pressing plate (12) is 1Cr18Ni9Ti; the material of the first sealing ring (2), the second sealing ring (5), the first sealing gasket (6) and the second sealing gasket (11) is polytetrafluoroethylene; and the material of the gasket 9 is T2.

9. A method for using the pressure and air tightness test fixture for a fairing support casing according to any one of claims 1 to 9, characterized in that: The following steps are included: Step 1: Loosen the C-type hexagon head clamping screw (13) and the hexagon nut (15) and hexagon flat nut (16) on the B-grade equal-length stud (14); Step 2: Install the fairing support casing into the test fixture, ensure that the inner casing stop of the fairing support casing fits with the stop of the bottom plate (1) to ensure coaxiality, install the cover plate (3), tighten the screws (4), and ensure that it fits tightly with the threaded hole of the rear wall plate of the fairing support casing; Step 3: Connect the adapter nozzle (10) to high-pressure air and observe the sealing of the weld.

10. The method for using the pressure and air tightness test fixture for the fairing support casing according to claim 9 is characterized in that: The test sealing performance of the support plate end face is ensured by tightening the C-type hexagonal head clamping screw (13) on the bow frame (8); the test sealing performance of the front wall plate of the fairing support casing is ensured by tightening the hexagonal nut on the B-level equal-length stud (14); the sealing performance of the threaded hole on the rear wall plate of the fairing support casing is ensured by tightening the screw (4); an air intake system is formed by the adapter nozzle (10), the first pressure plate (7) and the first sealing gasket (6), ensuring that high-pressure air enters the fairing support casing sealing cavity, thereby realizing underwater pressure airtightness inspection of the weld.

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