Water supply structure for water component circulation in aero-engine test

Abstract

The application belongs to the technical field of water component circulating water supply structure for aero-engine test, and particularly relates to a water component circulating water supply structure for aero-engine test, which comprises a protection cone, the inside of which is hollow, which is arranged in a nozzle opening and has a front end sleeved on the outer periphery of a water component; a water supply pipe, the inlet end of which is connected to a testbed water system, and the outlet end of which extends into the protection cone to connect the water component; a water supply hose, which is connected to the water supply pipe and located in the protection cone; a backwater pipe, the inlet end of which extends into the protection cone to connect the water component, and the outlet end of which is connected to the testbed water system, and the part of the backwater pipe located behind the nozzle opening is sleeved on the outer periphery of the water supply pipe; a backwater hose, which is connected to the backwater pipe and located in the protection cone; a connecting flange, which is sleeved on the backwater pipe and connected to the rear end of the protection cone through bolts; and a support, which is supported on the backwater pipe.

Description

Technical Field

[0001] This application belongs to the technical field of circulating water supply design for aero-engine test water components, specifically relating to a circulating water supply structure for aero-engine test water components. Background Technology

[0002] Aero-engine testing involves circulating water to water-using components, water cooling for these components, and thermal protection.

[0003] Currently, in aero-engine testing, water supply and return pipes are often connected to the water-using components and test bench water system by running through the internal support plate of the aero-engine. This allows for the circulation of water to the water-using components. This technical solution prevents the water supply and return pipes from directly contacting the high-temperature and high-pressure gases discharged from the aero-engine nozzle, ensuring the water-cooling and thermal protection of the water-using components. Furthermore, these components are not subjected to large thermal or aerodynamic loads and do not transmit large loads to the aero-engine, thus ensuring the performance of the aero-engine.

[0004] However, in some aero-engine tests, water-using components have a large water demand. Due to the limitation of the support plate size, the diameter of the water supply and return pipes cannot meet the large water demand of these components. In such cases, large-diameter pipes are designed for the water supply and return pipes, which are connected to the water-using components and the test bench water system through the aero-engine nozzle to circulate water to the components and meet their large water demand. However, this technical solution has the following drawbacks:

[0005] 1) The water supply pipe and return pipe are located in the high temperature and high pressure exhaust gas of the aircraft engine nozzle, which causes the water temperature in the water supply pipe and return pipe to rise, making it difficult to guarantee the water cooling and heat protection effect on the water-using components.

[0006] 2) The water supply and return pipes are subject to large thermal and aerodynamic loads, which will transfer large loads to the aero-engine and affect the performance of the aero-engine.

[0007] 3) Water supply and return pipes can interfere with the normal exhaust of aircraft engines and affect their performance.

[0008] This application is made in view of the aforementioned technical deficiencies.

[0009] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0010] The purpose of this application is to provide a circulating water supply structure for an aircraft engine test water component to overcome or mitigate at least one of the known technical defects.

[0011] The technical solution of this application is:

[0012] A circulating water supply structure for an aircraft engine test water component includes:

[0013] The protective cone is hollow inside and is installed in the nozzle, with its front end fitted around the water-using component.

[0014] The water supply pipe connects to the test bench water system at the inlet end and extends into the protective cone at the outlet end to connect to the water-using components.

[0015] The water supply hose is connected to the water supply pipe and is located in the protective cone;

[0016] The return water pipe has its inlet end extending into the protective cone to connect to the water-using components, and its outlet end connecting to the test bench water system. The part located after the nozzle is fitted around the outer periphery of the water supply pipe.

[0017] The return water hose connects to the return water pipe and is located within the protective cone;

[0018] Connect the flange, which is fitted onto the return water pipe, and connect the rear end of the protective cone with bolts;

[0019] The bracket is supported on the return water pipe.

[0020] According to at least one embodiment of this application, in the above-described circulating water supply structure for the aero-engine test water component, the portion of the return water pipe located after the nozzle is bent downwards.

[0021] According to at least one embodiment of this application, the above-described circulating water supply structure for aero-engine test water components further includes:

[0022] Insulation cotton is laid inside the protective cone.

[0023] According to at least one embodiment of this application, the above-described circulating water supply structure for aero-engine test water components further includes:

[0024] Gaskets are placed between the rear end of the protective cone and the connecting flange. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the circulating water supply structure for the aero-engine test water component provided in the embodiments of this application;

[0026] in:

[0027] 1-Protective cone; 2-Spray nozzle; 3-Water-using component; 4-Water supply pipe; 5-Water supply hose; 6-Return water pipe; 7-Return water hose; 8-Connecting flange; 9-Bracket; 10-Insulation cotton.

[0028] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0029] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0030] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0031] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0032] The following is in conjunction with the appendix Figure 1 This application will be described in further detail.

[0033] A circulating water supply structure for an aircraft engine test water component includes:

[0034] The protective cone 1 is hollow inside and is installed in the nozzle 2. Its front end can be a straight section fitted around the water-using component 3. Its shape can be modified with reference to the nozzle 2.

[0035] Water supply pipe 4, with its inlet end connected to the test bench water system and its outlet end extending into the protective cone 1 to connect to the water-using component 3;

[0036] Water supply hose 5 is connected to water supply pipe 4 and is located in protective cone 1;

[0037] The return water pipe 6 has its inlet end extending into the protective cone 1 to connect to the water supply component 3, and its outlet end connecting to the test bench water system. The part located after the nozzle 2 is fitted around the water supply pipe 4.

[0038] The return water hose 7 is connected to the return water pipe 6 and is located in the protective cone 1;

[0039] Connecting flange 8 is sleeved on return water pipe 6 and connected to the rear end of protective cone 1 by bolts;

[0040] Bracket 9 is supported on return water pipe 6.

[0041] Regarding the circulating water supply structure for the aero-engine test water component disclosed in the above embodiments, those skilled in the art will understand that its design connects the water supply component 3 and the test bench water system through the nozzle 2 via the water supply pipe 4 and the return water pipe 6, thereby circulating water to the water supply component 3. In aero-engine testing, it can meet the large water demand of the water supply component 3. Furthermore, the portion of the return water pipe 6 located after the nozzle 2 is fitted around the water supply pipe 4, allowing the return water from the return water pipe 6 to provide thermal protection for the water supply to the water supply pipe 4, preventing the water supply pipe 4 from directly contacting the high-temperature and high-pressure exhaust gas from the nozzle 2. In addition, a protective cone 1 is designed to provide thermal protection for the parts of the water supply pipe 4 and the return water pipe 6 near the water supply component 3, which can maintain a low water supply temperature, thereby ensuring the water cooling and thermal protection effect for the water supply component 3.

[0042] Regarding the circulating water supply structure for the aero-engine test water component disclosed in the above embodiments, those skilled in the art will understand that the protective cone 1 is installed in the nozzle 2 and is connected and supported by the bracket 9 through the return water pipe 6 and the connecting flange 8 using bolts. It has no mechanical connection with the nozzle 2 and will not transmit load to the aero-engine body. Furthermore, the protective cone is designed with a water supply hose 5 and a return water hose 7 connected to the water supply pipe 4 and the return water pipe 6. The load generated on the water supply pipe 4 and the return water pipe 6 can be released through deformation, avoiding the transmission of load to the water-using component 3, thereby ensuring the performance of the aero-engine.

[0043] Regarding the circulating water supply structure for the test water component of the aero-engine disclosed in the above embodiments, those skilled in the art will understand that the protective cone 1 set in the nozzle 2 surrounds the water supply pipe 4, the return water pipe 6 and the water-using component 3, which can guide the exhaust of the nozzle 2, thereby reducing interference with the normal exhaust of the aero-engine and thus affecting the performance of the aero-engine.

[0044] In some optional embodiments, in the above-mentioned circulating water supply structure for the aero-engine test water component, the portion of the return water pipe 6 located after the nozzle 2 is bent downwards to reduce the length of the return water pipe 6 in the direction of high-temperature and high-pressure exhaust from the nozzle 3. This prevents the temperature of the return water in the return water pipe 6 from rising significantly due to the high-temperature and high-pressure exhaust, which in turn leads to a significant increase in the temperature of the supply water in the supply water pipe 4, affecting the cooling and thermal protection effect on the water-using component 3.

[0045] In some optional embodiments, the above-described circulating water supply structure for aero-engine test water components further includes:

[0046] Insulation cotton 10 is laid inside the protective cone 1 to ensure the thermal protection effect on the parts of the water supply pipe 4 and the return pipe 6 that are close to the water-using components 3.

[0047] In some optional embodiments, the above-described circulating water supply structure for aero-engine test water components further includes:

[0048] A gasket is placed between the rear end of the protective cone 1 and the connecting flange 8.

[0049] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0050] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A circulating water supply structure for an aero-engine test water component, characterized in that, include: The protective cone (1) is hollow inside and is installed in the nozzle (2), with its front end fitted around the water-using component (3); Water supply pipe (4), the inlet end is connected to the test bench water system, and the outlet end extends into the protective cone (1) to connect to the water-using component (3); The water supply hose (5) is connected to the water supply pipe (4) and is located in the protective cone (1); The return water pipe (6) has its inlet end inserted into the protective cone (1) to connect to the water-using component (3), and its outlet end connected to the test bench water system. The part located behind the nozzle (2) is fitted around the water supply pipe (4). The return water hose (7) is connected to the return water pipe (6) and is located in the protective cone (1); Connect the flange (8), which is fitted onto the return water pipe (6) and connected to the rear end of the protective cone (1) by bolts; The bracket (9) is supported on the return water pipe (6).

2. The circulating water supply structure for aero-engine test water components according to claim 1, characterized in that, The portion of the return water pipe (6) located after the nozzle (2) bends downward.

3. The circulating water supply structure for aero-engine test water components according to claim 1, characterized in that, Also includes: Insulation cotton (10) is laid inside the protective cone (1).

4. The circulating water supply structure for aero-engine test water components according to claim 1, characterized in that, Also includes: A gasket is placed between the rear end of the protective cone (1) and the connecting flange (8).

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