An aero-engine test stand oil supply device and method with exhaust function

Abstract

An aero-engine test stand oil supply device and method with exhaust function, the oil supply device comprises a test stand, further comprising an oil depot, an oil tank, an oil gas separation tank and a recovery tank; the oil depot is used for storing aviation kerosene, and the oil depot is connected to the oil tank through a first oil pipeline; a pressure pump is connected to the oil tank through an air pipe; the oil tank is connected to the oil gas separation tank through a second oil pipeline; the oil gas separation tank is connected to the test stand through a third oil pipeline; the oil gas separation tank is further connected to the recovery tank through a fourth oil pipeline; a first valve is arranged on the first oil pipeline, a second valve is arranged on the third oil pipeline, and a third valve is arranged on the fourth oil pipeline; a shock device is arranged beside the second oil pipeline and used for shocking the oil pipeline. The shock device can shock the oil pipeline, and the aviation kerosene containing gas can be discharged into the recovery tank after the pressure pump is pressurized, so as to solve the problem of exhaust of the aero-engine test stand oil supply pipeline.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine test equipment technology, and in particular to an aircraft engine test stand fuel supply device and method with exhaust function. Background Technology

[0002] Aircraft engine tests use either No. 3 or No. 5 aviation kerosene, which is transported from the fuel depot to the test stand via pipelines. Power is provided by compressed gas. Because aviation kerosene is a flammable and explosive substance, its pipelines are buried underground. If gas enters the pipelines due to operational errors or other reasons, it will create numerous air bubbles in the aviation kerosene, leading to abnormal vibrations or test failures during the engine test, severely impacting the normal operation of the test. Furthermore, because a large amount of gas adheres to the inner walls of the pipelines, even prolonged flushing with large quantities of aviation kerosene may not completely remove it, creating potential hazards for subsequent test operations. Summary of the Invention

[0003] The main objective of this invention is to provide an oil supply device and method for an aircraft engine test stand with exhaust function, in order to solve the above-mentioned technical problems.

[0004] To achieve the above objectives, on the one hand, the present invention proposes an aero-engine test stand fuel supply device with exhaust function, including a test stand, an oil depot, an oil storage tank, an oil-gas separator, and a recovery tank; the oil depot is used to store aviation kerosene, and the oil depot is connected to the oil storage tank through a first oil supply pipe; a pressure pump is connected to the oil storage tank through an air pipe; the oil storage tank is connected to the oil-gas separator through a second oil supply pipe; the oil-gas separator is connected to the test stand through a third oil supply pipe; the oil-gas separator is also connected to the recovery tank through a fourth oil supply pipe; a first valve is provided on the first oil supply pipe, a second valve is provided on the third oil supply pipe, and a third valve is provided on the fourth oil supply pipe; a shock absorber is provided next to the second oil supply pipe for shocking the oil supply pipeline.

[0005] Preferably, the bottom wall of the oil depot is at an elevation higher than the top surface of the oil storage tank, and the aviation kerosene in the oil depot is added to the oil storage tank by gravity difference.

[0006] Preferably, the inlet end of the first oil pipeline is connected to the lower end of the side wall of the oil depot near the bottom wall.

[0007] Preferably, the outlet end of the first oil pipeline and the inlet end of the second oil pipeline are connected to the lower end of the side wall of the oil storage tank near the bottom wall.

[0008] On the other hand, the present invention also provides a fuel supply method for an aircraft engine test stand with exhaust function. Using the above-mentioned fuel supply device, the method includes the following steps: opening the first valve to allow aviation kerosene to be added into the oil storage tank by gravity difference, then closing the first valve and the third valve, opening the second valve, and pressurizing the gas by using a pressurizing pump to compress the gas so that the aviation kerosene in the oil storage tank enters the test stand in sequence through the second oil supply pipe, the oil-gas separator, and the third oil supply pipe.

[0009] Preferably, if the liquid level in the oil storage tank is lower than the inlet end of the second oil delivery pipe, a venting operation needs to be carried out when compressed gas enters the subsequent oil delivery pipeline, including the following steps:

[0010] Step S1: Open the first valve to allow aviation kerosene to be added back into the storage tank by gravity difference, so that the liquid level returns to the designated position;

[0011] Step S2: Close the first and second valves, open the third valve, turn on the shock absorber to shock the oil pipeline, turn on the pressurization pump, and compress the gas to discharge the aviation kerosene in the oil storage tank to the recovery tank through the oil-gas separator.

[0012] Step S3: Repeat step S2 until no more bubbles appear in the aviation kerosene flowing out of the recovery tank;

[0013] Step S4: Close the third valve and open the first valve to allow aviation kerosene to be added to the storage tank again using gravity difference; close the first and third valves, open the second valve, and use the pressurizing pump to pressurize and compress the gas so that the aviation kerosene in the storage tank passes through the second oil delivery pipe, the oil-gas separator, and the third oil delivery pipe in sequence into the test stand.

[0014] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0015] (1) In this invention, by setting up a shocker, combined with the structure of the oil-gas separator and the recovery tank, and combined with the opening and closing status of the first valve, the second valve and the third valve, the shocker can shock the oil pipeline. After the pressurizing pump pressurizes, the aviation kerosene containing gas can be discharged into the recovery tank, thus solving the problem of exhaust gas from the fuel supply pipeline of the aircraft engine test stand.

[0016] (2) In this invention, the bottom wall of the oil depot is at a higher elevation than the top surface of the oil storage tank. The aviation kerosene in the oil depot can be automatically added to the oil storage tank by utilizing the gravity difference, and the addition can be completed without additional power. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the fuel supply device for an aircraft engine test stand with exhaust function provided by the present invention.

[0019] Reference numerals: 100, Oil depot; 101, Oil storage tank; 102, Oil-gas separator; 103, Test bench; 104, Recovery tank; 105, First oil pipeline; 106, Second oil pipeline; 107, Third oil pipeline; 108, Fourth oil pipeline; 109, Gas pipeline; 110, First valve; 111, Second valve; 112, Third valve; 113, Booster pump; 114, Vibrator. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0022] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0023] Combination Figure 1As shown, an aircraft engine test stand fuel supply device with exhaust function includes a test stand 103, an oil depot 100, an oil storage tank 101, an oil-gas separator 102, and a recovery tank 104. The oil depot 100 is used to store aviation kerosene and is connected to the oil storage tank 101 via a first oil supply pipe 105. A pressure pump 113 is connected to the oil storage tank 101. The oil storage tank 101 is connected to the oil-gas separator 102 via a second oil supply pipe 106. The gas separator 102 is connected to the test stand 103 via the third oil pipeline 107; the oil-gas separator 102 is also connected to the recovery tank 104 via the fourth oil pipeline 108; a first valve 110 is installed on the first oil pipeline 105, a second valve 111 is installed on the third oil pipeline 107, and a third valve 112 is installed on the fourth oil pipeline 108; a vibrator 114 is installed next to the second oil pipeline 106 for vibrating the oil pipeline.

[0024] In this embodiment, the bottom wall of the oil depot 100 is at a higher elevation than the top surface of the oil storage tank 101. Aviation kerosene in the oil depot 100 is added to the oil storage tank 101 using gravity. The inlet end of the first oil delivery pipe 105 is connected to the lower end of the side wall of the oil depot 100 near the bottom wall. Addition can be completed using gravity, requiring no additional power.

[0025] In this embodiment, the outlet end of the first oil pipeline 105 and the inlet end of the second oil pipeline 106 are connected to the lower end of the side wall of the oil storage tank 101 near the bottom wall. With this structure, the compressed gas can be pressurized by the pressure pump 113, allowing the aviation kerosene in the oil storage tank 101 to enter the second oil pipeline 106 more effectively.

[0026] On the other hand, this embodiment also provides a fuel supply method for an aircraft engine test stand with exhaust function. Using the above-mentioned fuel supply device, the method includes the following steps: opening the first valve 110 to allow aviation kerosene to be added into the oil storage tank 101 by gravity difference; then closing the first valve 110 and the third valve 112, opening the second valve 111, and pressurizing the gas using the pressurizing pump 113. The compressed gas causes the aviation kerosene in the oil storage tank 101 to enter the test stand 103 sequentially through the second oil supply pipe 106, the oil-gas separator 102, and the third oil supply pipe 107.

[0027] If the liquid level in the oil storage tank 101 is lower than the inlet end of the second oil delivery pipe 106, when compressed gas enters the subsequent oil delivery pipeline, an exhaust operation must be carried out, including the following steps:

[0028] Step S1: Open the first valve 110 to allow aviation kerosene to be added back into the oil storage tank 101 by gravity difference, so that the liquid level is restored to the designated position;

[0029] Step S2: Close the first valve 110 and the second valve 111, open the third valve 112, turn on the shock absorber 114 to shock the oil pipeline, turn on the pressurization pump 113, and compress the gas to discharge the aviation kerosene in the oil storage tank 101 to the recovery tank 104 through the oil-gas separator 102.

[0030] Step S3: Repeat step S2 until there are no more bubbles in the aviation kerosene flowing out of the recovery tank 104;

[0031] Step S4: Close the third valve 112 and open the first valve 110 to allow aviation kerosene to be added to the storage tank 101 again by gravity difference; close the first valve 110 and the third valve 112, open the second valve 111, and use the pressurizing pump 113 to pressurize and compress the gas so that the aviation kerosene in the storage tank 101 enters the test stand 103 through the second oil delivery pipe 106, the oil-gas separator 102, and the third oil delivery pipe 107 in sequence.

[0032] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A fuel supply method for an aircraft engine test stand with exhaust function, characterized in that, The fuel supply system of the aircraft engine test stand with exhaust function includes the test stand (103), as well as the oil depot (100), the oil storage tank (101), the oil-gas separator (102) and the recovery tank (104). The oil depot (100) is used to store aviation kerosene. The oil depot (100) is connected to the oil storage tank (101) via a first oil pipeline (105). A booster pump (113) is connected to the oil storage tank (101). The oil storage tank (101) is connected to the oil-gas separator (102) via a second oil pipeline (106). The oil-gas separator (102) is connected to the test stand (103) via a third oil pipeline (107). The oil-gas separator (102) is also connected to the recovery tank (104) via a fourth oil pipeline (108). A first valve (110) is provided on the first oil pipeline (105), a second valve (111) is provided on the third oil pipeline (107), and a third valve (112) is provided on the fourth oil pipeline (108). A shock absorber (114) is provided next to the second oil pipeline (106) for shocking the oil pipeline; The bottom wall of the oil depot (100) is at an elevation higher than the top surface of the oil storage tank (101). The aviation kerosene in the oil depot (100) is added to the oil storage tank (101) by gravity difference. The fuel supply method includes the following steps: Open the first valve (110) to allow aviation kerosene to be injected into the storage tank (101) by gravity difference. Then close the first valve (110) and the third valve (112), open the second valve (111), and use the pressurizing pump (113) to pressurize and compress the gas so that the aviation kerosene in the storage tank (101) passes through the second oil pipeline (106), the oil-gas separator (102), and the third oil pipeline (107) into the test stand (103). If the liquid level in the oil storage tank (101) is lower than the inlet end of the second oil pipeline (106), when compressed gas enters the subsequent oil pipeline, an exhaust operation needs to be carried out, including the following steps: Step S1: Open the first valve (110) to allow aviation kerosene to be added back into the oil storage tank (101) by gravity difference, so that the liquid level is restored to the designated position; Step S2: Close the first valve (110) and the second valve (111), open the third valve (112), turn on the shock absorber (114) to shock the oil pipeline, turn on the pressurizing pump (113), and compress the gas to discharge the aviation kerosene in the oil storage tank (101) to the recovery tank (104) through the oil-gas separator (102). Step S3: Repeat step S2 until no more bubbles appear in the aviation kerosene flowing out of the recovery tank (104); Step S4: Close the third valve (112) and open the first valve (110) to allow aviation kerosene to be added to the storage tank (101) again by gravity difference; close the first valve (110) and the third valve (112), open the second valve (111), and use the pressurizing pump (113) to pressurize and compress the gas so that the aviation kerosene in the storage tank (101) passes through the second oil pipeline (106), the oil-gas separator (102), and the third oil pipeline (107) into the test stand (103).

2. The fuel supply method for an aero-engine test stand with exhaust function as described in claim 1, characterized in that, The inlet end of the first oil pipeline (105) is connected to the lower end of the side wall of the oil depot (100) near the bottom wall.

3. The fuel supply method for an aircraft engine test stand with exhaust function as described in claim 1, characterized in that: The outlet end of the first oil pipeline (105) and the inlet end of the second oil pipeline (106) are connected to the lower end of the side wall of the oil storage tank (101) near the bottom wall.

Images