An aerospace fuel pump test gearbox

Abstract

The present invention provides an aerospace fuel pump test gearbox, comprising: a cantilevered housing, the cantilever end of the housing extending into a vacuum test chamber; a sealing cover disposed on the outer surface of the housing, surrounding the housing and configured to seal against the chamber wall of the vacuum test chamber; an axial sealing ring and a radial sealing ring sequentially embedded on the mating surface of the sealing cover for mating with the vacuum test chamber; a transmission shaft supported by the housing, one end of the transmission shaft connected to an input flange, the other end of the transmission shaft extending beyond the end cap of the cantilever end of the housing and connected to an output spline sleeve configured to connect to the shaft head of an aerospace fuel pump to load the aerospace fuel pump; and a bracket secured to the end cap of the cantilever end of the housing for securing the aerospace fuel pump. This aerospace fuel pump test gearbox is capable of testing aerospace fuel pumps in a vacuum test chamber environment.

Description

Technical Field

[0001] The present invention relates to the technical field of gear boxes, and in particular to an aerospace fuel pump test gear box. Background Art

[0002] Aerospace fuel pumps are essential components of aircraft fuel systems, typically installed inside the fuel tank to provide fuel at the required flow rate and pressure to the engine inlet. As the aircraft's fuel delivery equipment, the safety and reliability of aerospace fuel pumps are directly related to the safety of the aircraft. Therefore, aerospace fuel pumps must be tested on test benches to ensure they meet acceptable quality standards.

[0003] Currently, conventional fuel pumps are typically tested in conventional environments. However, aerospace fuel pumps must be tested in a vacuum chamber. This requires the test gearbox to be placed deep within the chamber and to be well sealed both within the chamber and within the test chamber. Currently, such a gearbox has not been publicly released.

[0004] Therefore, how to provide an aerospace fuel pump test gearbox to implement the test of the aerospace fuel pump in a vacuum test chamber environment has become a technical problem that needs to be solved urgently by those skilled in the art. Summary of the Invention

[0005] In view of this, an object of the present invention is to provide an aerospace fuel pump test gearbox to implement testing of aerospace fuel pumps in a vacuum test chamber environment.

[0006] In order to achieve the above object, the present invention provides an aerospace fuel pump test gearbox, comprising:

[0007] A cantilever-supported box, the cantilever end of which is adapted to extend into a vacuum test chamber, the outer surface of which is provided with a sealing cover which surrounds the box and is adapted to seal against the chamber wall of the vacuum test chamber, the sealing cover having an axial sealing ring and a radial sealing ring sequentially embedded on the mating surface thereof for mating with the vacuum test chamber;

[0008] A transmission shaft supported on the housing, one end of the transmission shaft being connected to an input flange, and the other end of the transmission shaft extending out of an end cap of the cantilever end of the housing and connected to an output spline sleeve, the output spline sleeve being used to connect to a shaft head of an aerospace fuel pump to load the aerospace fuel pump;

[0009] And, a bracket fixed to the end cover of the cantilever end of the box body for fixing the aerospace fuel pump, the bracket has a fuel pump interface for fixing the shell of the aerospace fuel pump, when the aerospace fuel pump to be tested is fixed on the fuel pump interface, the bracket forms a sealing cavity that can seal the output spline sleeve.

[0010] Preferably, the fuel pump interface is a first-level stepped hole, and the housing of the aerospace fuel pump to be tested is a first-level stepped boss that matches the shape of the fuel pump interface;

[0011] The housing of the aerospace fuel pump to be tested is matched with the fuel pump interface and fixed together by a clamping ring. The clamping ring has a trapezoidal groove. The housing of the aerospace fuel pump to be tested and the bracket have wedge-shaped surfaces that match the groove.

[0012] Preferably, an O-ring is provided between the housing of the aerospace fuel pump to be tested and the bracket.

[0013] Preferably, the bracket is provided with an oil inlet channel and an oil return channel communicating with the cavity of the bracket;

[0014] A first oil injection port communicating with the oil inlet channel is provided on the inner wall of the bracket, and the oil injection direction of the first oil injection port is toward the connection portion between the output spline sleeve and the shaft head of the aerospace fuel pump to be tested;

[0015] A second oil injection port communicating with the oil inlet channel is further provided on the inner wall of the bracket, and the oil injection direction of the second oil injection port is toward the inner wall of the bracket itself;

[0016] A third oil injection port connected to the oil inlet channel is further provided on the inner wall of the bracket, and the oil injection direction of the third oil injection port is toward the transmission shaft.

[0017] Preferably, the box body is cantilever supported on a mounting base;

[0018] The mounting seat includes a base and two support plates fixed on the base and arranged at intervals along the axial direction of the transmission shaft, and the box body is fixed on the two support plates.

[0019] Preferably, a reinforcing rib plate is connected between the two support plates.

[0020] Preferably, the box body is supported on the support plate close to the vacuum test chamber by four-point screws.

[0021] Preferably, the transmission shaft is supported on the housing via a precision bearing, and a pressure plate and a spring for applying a preload force to the precision bearing are disposed on the axial outer side of the precision bearing;

[0022] The pressure plate is fixed on the box body, and the spring is compressed and arranged between the pressure plate and the precision bearing.

[0023] Preferably, the box body is provided with a lubricating oil passage communicating with the precision bearing so as to supply lubricating oil to the precision bearing.

[0024] The present invention has the following beneficial effects:

[0025] In actual use, the aerospace fuel pump test gearbox has the housing of the test aerospace fuel pump fixed to the fuel pump interface of the bracket, and the shaft head of the aerospace fuel pump is connected to the output spline sleeve on the drive shaft, thereby achieving loading of the aerospace fuel pump. Because aerospace fuel pump testing requires a vacuum environment, the aerospace fuel pump test gearbox housing is supported by a cantilever. The cantilever end of the housing extends into the vacuum test chamber, and the sealing cover on the housing seals with the chamber wall, thus enabling the aerospace fuel pump to be tested in a vacuum test chamber environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments and descriptions of the present application are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0027] Figure 1 This is a schematic structural diagram of the aerospace fuel pump test gearbox according to the present invention;

[0028] Figure 2 This is a schematic structural diagram of the aerospace fuel pump to be tested according to the present invention being fixed on a bracket;

[0029] Figure 3 A schematic diagram of the structure of the precision bearing of the present invention configured with a pressure plate and a spring;

[0030] Figure Numbers

[0031] 1-housing; 2-drive shaft; 3-end cover; 4-bracket; 5-vacuum test chamber; 6-sealing cover; 7-axial sealing ring; 8-radial sealing ring; 9-input flange; 10-output spline sleeve; 11-housing; 12-retaining ring; 13-O-ring; 14-oil inlet channel; 15-oil return channel; 16-first oil injection port; 17-second oil injection port; 18-third oil injection port; 19-base; 20-support plate; 21-four-point screw; 22-precision bearing; 23-pressure plate; 24-spring; 25-lubricating oil channel. DETAILED DESCRIPTION

[0032] The core of the present invention is to provide an aerospace fuel pump test gearbox to realize the test of the aerospace fuel pump in a vacuum test chamber environment.

[0033] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0034] An embodiment of the present invention discloses an aerospace fuel pump test gearbox, comprising a cantilevered housing 1, a drive shaft 2 supported on the housing 1, and a bracket 4 fixed to an end cap 3 at the cantilevered end of the housing 1. The cantilevered end of the housing 1 is configured to extend into a vacuum test chamber 5. A sealing cover 6 is provided on the outer surface of the housing 1, surrounding the housing 1 and configured to seal against the walls of the vacuum test chamber 5. An axial sealing ring 7 and a radial sealing ring 8 are sequentially embedded on the mating surface of the sealing cover 6 for mating with the vacuum test chamber 5. The axial sealing ring 7 seals the vacuum test chamber 5 in the axial direction, while the radial sealing ring 8 seals the vacuum test chamber 5 in the radial direction.

[0035] The transmission shaft 2 is supported on the box body 1. One end of the transmission shaft 2 is connected to the input flange 9 to receive power. The other end of the transmission shaft 2 extends out of the end cover 3 of the cantilever end of the box body 1 and is connected to the output spline sleeve 10. The output spline sleeve 10 is used to connect with the shaft head of the aerospace fuel pump to be tested to load the aerospace fuel pump.

[0036] Bracket 4 is fixed to the end cap 3 at the cantilever end of the housing 1 and is used to secure the aerospace fuel pump to be tested. Specifically, bracket 4 has a fuel pump interface for securing the aerospace fuel pump housing 11. When the aerospace fuel pump to be tested is secured to the fuel pump interface, bracket 4 forms a sealed cavity that seals the output spline sleeve 10.

[0037] In actual use, the aerospace fuel pump test gearbox has its housing 11 secured to the fuel pump interface of the bracket 4. The pump's shaft head is then connected to the output splined sleeve 10 on the drive shaft 2, thereby enabling loading of the aerospace fuel pump. Because aerospace fuel pump testing requires a vacuum environment, the gearbox's housing 1 is cantilevered, with the cantilevered end of the housing 1 extending into the vacuum test chamber 5. The sealing cover 6 on the housing 1 seals against the chamber wall of the vacuum test chamber 5, enabling testing of the aerospace fuel pump within the vacuum test chamber.

[0038] In some specific embodiments, such as Figure 2As shown, the fuel pump interface is a single-stepped hole, and the housing 11 of the aerospace fuel pump to be tested is a single-stepped boss that matches the shape of the fuel pump interface. After the housing 11 and the fuel pump interface are shaped to match, they are secured together by a retaining ring 12. Retaining ring 12 has a trapezoidal groove, and the housing 11 of the aerospace fuel pump to be tested and the bracket 3 have wedge-shaped surfaces that match the groove. By providing the fuel pump interface on bracket 4 and securing the housing 11 of the aerospace fuel pump to bracket 4 via retaining ring 12, the fuel pump can be easily secured to bracket 4, making installation simple and convenient for testing.

[0039] In some specific implementation schemes, an O-ring 13 is provided between the housing 11 of the aerospace fuel pump to be tested and the bracket 4. In this way, a seal between the housing 11 of the aerospace fuel pump and the bracket 4 is achieved.

[0040] In some more specific embodiments, bracket 4 is provided with an oil inlet channel 14 and an oil return channel 15, both communicating with the cavity of bracket 3. A first oil injection port 16, communicating with oil inlet channel 14, is provided on the inner wall of bracket 4. First oil injection port 16 sprays oil toward the connection between output splined sleeve 10 and the shaft head of the aerospace fuel pump to be tested. The first oil injection port provides lubrication and cooling for the splined connection.

[0041] A second oil injection port 17, connected to the oil inlet channel, is also provided on the inner wall of the bracket 4. This second oil injection port 17 sprays oil toward the inner wall of the bracket 4 itself. Because the temperature inside the vacuum test chamber 5 varies widely, typically between -60°C and 220°C, oil cooling is performed on the inner surface of the bracket 4 through the second oil injection port, preventing the high temperature of the external environment from being transmitted through the chamber to the drive shaft bearings.

[0042] A third oil injection port 18 communicating with the oil inlet channel is further provided on the inner wall of the bracket 4. The oil injection direction of the third oil injection port 18 is toward the transmission shaft 2. The transmission shaft 2 is cooled by spraying oil through the oil injection port.

[0043] In other specific embodiments, the housing 1 is cantilevered on a mounting base. The mounting base includes a base 19 and two support plates 20 fixed to the base 19 and spaced apart along the axial direction of the transmission shaft 2. The housing 1 is fixed to the two support plates 20. This two-point support ensures the housing's support stability and reduces gearbox vibration caused by the cantilever support.

[0044] More preferably, a stiffening plate is connected between the two support plates 20 to increase the overall rigidity of the mounting base, making the whole base more secure.

[0045] In some other specific embodiments, the box body 1 is supported on a support plate 2 close to the vacuum test chamber by four-point screws 21 , thereby ensuring the support stability of the box body 1 .

[0046] In some specific embodiments, such as Figure 1 and Figure 3 As shown, the transmission shaft 2 is supported on the housing 1 via a precision bearing 22. A pressure plate 23 and a spring 24 are disposed axially outward of the precision bearing 22 to apply a preload force to the precision bearing 22. The pressure plate 23 is fixed to the housing 1, and the spring 24 is compressed and disposed between the pressure plate 23 and the precision bearing 22. The precision bearing can have a dimensional accuracy of P4 and an operating accuracy of P2. The configuration of the spring 24 ensures an appropriate preload force on the precision bearing 22, thereby extending the lifespan and speed of the precision bearing 22.

[0047] In some other specific embodiments, the housing 1 is provided with a lubricating oil passage 25 communicating with the precision bearing 22 , so as to allow lubricating oil to flow into the precision bearing 22 , thereby achieving the purpose of lubricating the precision bearing 22 .

[0048] It should be noted that the various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same and similar parts between the various embodiments can be referenced to each other.

[0049] It should be understood that the use of "system," "device," "unit," and / or "module" in this application is merely a method for distinguishing different components, elements, parts, portions, or assemblies at different levels. However, if other terms can achieve the same purpose, the terms may be replaced by other expressions.

[0050] As used in this application and the claims, unless the context clearly indicates an exception, the terms "a," "an," "an," and / or "the" are not intended to refer to the singular and may include the plural, unless the context clearly indicates otherwise. Generally speaking, the terms "comprises" and "include" only indicate the inclusion of the steps and elements specifically identified, and these steps and elements do not constitute an exclusive list. A method or apparatus may also include other steps or elements. The phrase "comprises a..." does not preclude the presence of additional identical elements in the process, method, product, or apparatus that includes the elements.

[0051] In the description of the embodiments of this application, unless otherwise specified, " / " represents or. For example, A / B can represent A or B. "And / or" in this article is simply a description of the association relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, in the description of the embodiments of this application, "plurality" means two or more than two.

[0052] In the following, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the quantity of the technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the features.

[0053] If a flow chart is used in this application, the flow chart is used to illustrate the operations performed by the system according to the embodiments of the application. It should be understood that the previous or subsequent operations are not necessarily performed in exact order. Instead, the steps can be processed in reverse order or simultaneously. At the same time, other operations can be added to these processes, or one or more operations can be removed from these processes.

[0054] This document uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the core ideas of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from the principles of the present invention, and such improvements and modifications also fall within the scope of protection of the claims of the present invention.

Claims

1. An aerospace fuel pump test gearbox, characterized in that: include: A cantilever-supported box, the cantilever end of which is adapted to extend into a vacuum test chamber, the outer surface of which is provided with a sealing cover which surrounds the box and is adapted to seal against the chamber wall of the vacuum test chamber, the sealing cover having an axial sealing ring and a radial sealing ring sequentially embedded on the mating surface thereof for mating with the vacuum test chamber; A transmission shaft supported on the housing, one end of the transmission shaft being connected to an input flange, and the other end of the transmission shaft extending out of an end cap of the cantilever end of the housing and connected to an output spline sleeve, the output spline sleeve being used to connect to a shaft head of an aerospace fuel pump to load the aerospace fuel pump; and a bracket fixed to the end cover of the cantilever end of the box body for fixing an aerospace fuel pump, the bracket having a fuel pump interface for fixing the housing of the aerospace fuel pump, and when the aerospace fuel pump to be tested is fixed to the fuel pump interface, the bracket forms a sealing cavity capable of sealing the output spline sleeve; The bracket is provided with an oil inlet channel and an oil return channel communicating with the cavity of the bracket; A first oil injection port communicating with the oil inlet channel is provided on the inner wall of the bracket, and the oil injection direction of the first oil injection port is toward the connection portion between the output spline sleeve and the shaft head of the aerospace fuel pump to be tested; A second oil injection port communicating with the oil inlet channel is further provided on the inner wall of the bracket, and the oil injection direction of the second oil injection port is toward the inner wall of the bracket itself; A third oil injection port connected to the oil inlet channel is further provided on the inner wall of the bracket, and the oil injection direction of the third oil injection port is toward the transmission shaft.

2. The aerospace fuel pump test gearbox according to claim 1, characterized in that: The fuel pump interface is a first-level stepped hole, and the housing of the aerospace fuel pump to be tested is a first-level stepped boss that matches the shape of the fuel pump interface; The housing of the aerospace fuel pump to be tested is matched with the fuel pump interface and fixed together by a clamping ring. The clamping ring has a trapezoidal groove. The housing of the aerospace fuel pump to be tested and the bracket have wedge-shaped surfaces that match the groove.

3. The aerospace fuel pump test gearbox according to claim 2, characterized in that: An O-type sealing ring is provided between the housing of the aerospace fuel pump to be tested and the bracket.

4. The aerospace fuel pump test gearbox according to claim 1, characterized in that: The box body is cantilevered and supported on a mounting base; The mounting seat includes a base and two support plates fixed on the base and arranged at intervals along the axial direction of the transmission shaft, and the box body is fixed on the two support plates.

5. The aerospace fuel pump test gearbox according to claim 4, characterized in that: A reinforcing rib plate is connected between the two support plates.

6. The aerospace fuel pump test gearbox according to claim 4, characterized in that: The box body is supported on the support plate close to the vacuum test chamber by four-point screws.

7. The aerospace fuel pump test gearbox according to claim 1, characterized in that: The transmission shaft is supported on the housing via a precision bearing, and a pressure plate and a spring for applying a preload force to the precision bearing are arranged on the axial outer side of the precision bearing; The pressure plate is fixed on the box body, and the spring is compressed and arranged between the pressure plate and the precision bearing.

8. The aerospace fuel pump test gearbox according to claim 7, characterized in that: The box body is provided with a lubricating oil passage communicated with the precision bearing so as to supply lubricating oil to the precision bearing.

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