A device for testing bleed air from an aircraft engine

Abstract

The application discloses a device for airplane engine bleed air test, and relates to the technical field of airplane maintenance, which aims at solving the problem that the existing airplane engine bleed air test device needs to frequently adjust the bleed air pipe and is not provided with a redundant air chamber, which is easy to cause damage to the airplane engine bleed air system. The device comprises an air inlet assembly, a redundant air chamber, a bleed air branch pipe and a detection terminal. The air inlet assembly comprises an air inlet pump, an air inlet adjusting valve and an air inlet chamber. The redundant air chamber comprises an air inlet and an air outlet, which are arranged at one end of the redundant air chamber. The bleed air branch pipe comprises a first bleed air branch pipe and a second bleed air branch pipe. The detection terminal comprises an emergency pressure relief valve, a connecting branch pipe, a standby branch pipe and a detection box. The first bleed air branch pipe and the second bleed air branch pipe are arranged, and a separate adjusting valve control mode is adopted, so that the bleed air system can be detected in multiple modes, and the bleed air pipe can be replaced frequently in different detection stages.

Description

Technical Field

[0001] This invention relates to the field of aircraft maintenance technology, specifically to a device for testing bleed air in aircraft engines. Background Technology

[0002] Aircraft engine bleed air testing equipment is used to test the bleed air system of an aircraft engine. Generally, the bleed air test equipment is connected to the engine to be tested by connecting the bleed air pipe of the bleed air test equipment to the other end of the bleed air pipe, and then connected to the test element, so as to test various data of the aircraft engine bleed air system and determine whether the bleed air system is qualified.

[0003] For example, patent CN214667661U, entitled "A Device for Bleed Air Testing of Aircraft Engines," includes a pressure gauge, connecting pipe, ball valve, needle valve, and pneumatic pressure reducing valve. It also includes a toolbox with a partition fixedly connected to it, dividing the toolbox into a first space and a second space. The first space houses the connecting pipe, and the second space houses the pressure gauge, ball valve, needle valve, and pneumatic pressure reducing valve. In the second space, a third right-angled plate is located on the inner side of the toolbox opposite the partition, fixedly connected to the toolbox via its vertical edge. The toolbox also contains a panel fixed to the upper part of the partition and the horizontal edge of the second right-angled plate. The pressure gauge, ball valve, needle valve, and pneumatic pressure reducing valve are respectively fixed to the panel.

[0004] Existing aircraft engine bleed air testing equipment requires adjustments to the intake air temperature and intake air source according to the testing stage when testing the bleed air system. This necessitates frequent replacement and adjustment of the bleed air pipe. Furthermore, no redundant air chamber is provided during bleed air system testing. If the bleed air pipe becomes blocked, it can easily damage the aircraft engine's bleed air system, and in severe cases, cause irreversible damage to the aircraft engine's intake system. Summary of the Invention

[0005] The purpose of this invention is to provide a device for testing bleed air in aircraft engines, in order to solve the problems mentioned in the background art, such as the need for frequent adjustment of the bleed air pipe and the lack of redundant air chambers in existing aircraft engine bleed air testing devices, which can easily cause damage to the aircraft engine bleed air system.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a device for testing bleed air in an aircraft engine, comprising: an intake assembly, the intake assembly including an intake pump, an intake regulating valve and an intake chamber, the intake pump being disposed at one end of the intake assembly, the intake regulating valve being connected at one end to the intake pump and at the other end to the intake chamber, the intake chamber including a first bleed air inlet and a first bleed air outlet, the first bleed air inlet being connected to the intake regulating valve, and the first bleed air outlet being disposed at one side end of the intake chamber;

[0007] A redundant gas chamber, the redundant gas chamber including an air inlet and an air outlet, the air inlet and the air outlet being located at one end of the redundant gas chamber;

[0008] The air intake branch pipe includes a first air intake branch pipe and a second air intake branch pipe. One end of the first air intake branch pipe is connected to a first air intake outlet, and the other end is connected to an air inlet. One end of the second air intake branch pipe is connected to an air outlet.

[0009] The detection terminal includes an emergency pressure relief valve, a connecting branch pipe, a spare branch pipe, and a detection box. The connecting branch pipe is connected to a second air intake branch pipe. The emergency pressure relief valve is located on the connecting branch pipe near one end of the second air intake branch pipe. The spare branch pipe is connected to the second air intake branch pipe. The detection box is located on one side of the connecting branch pipe and is used to detect the fluid pressure inside the connecting branch pipe.

[0010] The air intake chamber also includes a pressure relief branch pipe, which is located at one end of the bottom of the air intake chamber. The pressure relief branch pipe includes a pressure relief regulating valve, which is located at the end of the pressure relief branch pipe away from the air intake chamber.

[0011] One end of the first air intake branch pipe is detachably connected to the first air intake outlet, and the first air intake branch pipe is detachably connected to the air inlet.

[0012] The redundant gas chamber also includes a sealing cover, which is located at the end of the redundant gas chamber where there is no air inlet and air outlet.

[0013] The second air intake branch pipe also includes a second air intake regulating valve at the end near the detection terminal.

[0014] Preferably, a backflow shut-off valve is provided at one end of the air intake branch pipe near the redundant air chamber.

[0015] Preferably, the backup branch pipe includes a backup regulating valve and a second normally open manual regulating valve. The backup regulating valve is located at one end of the backup branch pipe near the second bleed branch pipe, and the second normally open manual regulating valve is located at one end of the backup branch pipe away from the second bleed branch pipe.

[0016] Preferably, the connecting branch pipe further includes a connecting regulating valve and a first normally open manual regulating valve. The connecting regulating valve is located on the connecting branch pipe near the emergency pressure relief valve, and the first normally open manual regulating valve is located on the connecting branch pipe away from the emergency pressure relief valve.

[0017] Preferably, the first and second air intake branches are made of high-pressure resistant stainless steel.

[0018] Preferably, the connecting branch pipe and the spare branch pipe are made of high-pressure resistant stainless steel.

[0019] Compared with the prior art, the beneficial effects of the present invention are:

[0020] This invention enables multi-mode testing of the bleed air system by setting up a first bleed air branch pipe and a second bleed air branch pipe, and controlling them with separate regulating valves. This avoids the need to frequently replace the bleed air branch pipe at different stages of testing, thereby improving the testing efficiency of the aircraft engine bleed air system and saving testing time and labor costs.

[0021] This invention, by setting up an air intake chamber and a redundant air chamber, avoids bleed air system failures caused by malfunctions in the air intake pump or air intake regulating valve during bleed air testing, effectively ensuring that the aircraft engine will not be damaged during bleed air testing and effectively reducing the damage to the aircraft engine during testing.

[0022] This invention avoids damage to the air intake system due to excessive pressure during testing by setting up a branch pipe and an emergency pressure relief valve. It also installs a sealing cover in the redundant air chamber to facilitate the cleaning of dust and other impurities in the redundant air chamber, thus preventing the air intake system from being affected by dust or impurities. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 This is a schematic diagram illustrating the structure of the intake assembly of the present invention;

[0025] Figure 3 This is a schematic diagram showing one side view of the pipeline in this invention;

[0026] Figure 4 This is a schematic diagram showing the pipeline from another side of the present invention.

[0027] In the diagram: 100, intake assembly; 110, intake pump; 120, intake regulating valve; 130, intake chamber; 131, first bleed air inlet; 132, first bleed air outlet; 133, pressure relief branch pipe; 134, pressure relief regulating valve; 200, redundant air chamber; 210, air inlet; 220, air outlet; 230, sealing cap; 300, bleed air branch pipe; 310, first bleed air branch pipe; 320, second bleed air branch pipe; 321, second bleed air regulating valve; 322, reflux shut-off valve; 400, detection terminal; 410, emergency pressure relief valve; 420, connecting branch pipe; 421, connecting regulating valve; 422, first normally open manual regulating valve; 430, spare branch pipe; 431, spare regulating valve; 432, second normally open manual regulating valve; 440, detection box. Detailed Implementation

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Example 1

[0029] Please see Figures 1-3 One embodiment of the present invention includes:

[0030] The intake assembly 100 includes an intake pump 110, an intake regulating valve 120, and an intake chamber 130. The intake pump 110 is located at one end of the intake assembly 100 and is driven by a motor or other drive equipment. The intake pump 110 compresses outside air and sends it to the intake regulating valve 120. One end of the intake regulating valve 120 is connected to the intake pump 110, and the other end is connected to the intake chamber 130. The intake volume can be adjusted by the intake regulating valve 120 to meet the intake volume required for aircraft engine intake testing. The intake chamber 130 includes a first bleed air inlet 131 and a first bleed air outlet 132. The inlet 131 is connected to the intake regulating valve 120. The first bleed outlet 132 is located at one end of the side of the intake chamber 130. The intake chamber 130 also includes a pressure relief branch pipe 133, which is located at one end of the bottom of the intake chamber 130. The pressure relief branch pipe 133 includes a pressure relief regulating valve 134, which is located at the end of the pressure relief branch pipe 133 away from the intake chamber 130. By setting a pressure relief branch pipe at one end of the bottom of the intake chamber 130, the fluid in the intake chamber 130 is output in time when the bleed pipe is blocked or the intake chamber 130 is overpressurized, so as to avoid affecting the subsequent bleed system and effectively prevent further losses.

[0031] The redundant air chamber 200 includes an air inlet 210 and an air outlet 220, which are located at one end of the redundant air chamber 200. The redundant air chamber 200 is made of rigid material and can withstand at least 10 atmospheres of pressure. The air inlet 210 and air outlet 220 can be arranged along the side wall of the redundant air chamber 200. The air inlet 210 and air outlet 220 should not be too close to avoid uneven stress on the chamber wall, which could cause the chamber to burst. The redundant air chamber 200 also includes a sealing cover 230, which is located at the end of the redundant air chamber 200 where the air inlet 210 and air outlet 220 are not located. The sealing cover 230 is a normally closed sealing cover. The redundant air chamber 200 can be opened through the sealing cover 230 for emergency air release or cleaning of the chamber after testing, to prevent dust accumulation inside the redundant air chamber 200, which could affect the testing of the aircraft engine bleed air system.

[0032] The air intake branch pipe 300 includes a first air intake branch pipe 310 and a second air intake branch pipe 320. One end of the first air intake branch pipe 310 is connected to the first air intake outlet 132, and the other end is connected to the air inlet 210. One end of the second air intake branch pipe 320 is connected to the air outlet 220. One end of the first air intake branch pipe 310 and the first air intake outlet 132 are detachably connected, and the first air intake branch pipe 310 and the air inlet 210 are detachably connected. In this embodiment, the detachable connection between the first air intake branch pipe 310 and the first air intake outlet 132 and the air inlet 210 is a flange connection. It is easy to understand that in other embodiments, other connection methods, such as threads, can be used. The method enables detachable connection; the second bleed air branch pipe 320 near the detection terminal 400 also includes a second bleed air regulating valve 321, through which other fluid sources, such as nitrogen or cryogenic gas, can be supplied into the second bleed air branch pipe 320, to realize multi-type detection of the aircraft engine bleed air system, avoid the need to replace multiple bleed air pipes to complete the detection, and improve the detection efficiency of the bleed air system. The bleed air branch pipe 300 near the redundant gas chamber 200 is provided with a backflow stop valve 322. By setting the backflow stop valve 322, fluid backflow to the redundant gas chamber 200 is prevented, so as to cooperate with the detection of different fluid sources of the bleed air system by the second bleed air branch pipe 320 alone.

[0033] The detection terminal 400 includes an emergency pressure relief valve 410, a connecting branch pipe 420, a spare branch pipe 430, and a detection box 440. The connecting branch pipe 420 is connected to the second bleed air branch pipe 320. The emergency pressure relief valve 410 is located on the connecting branch pipe 420 near one end of the second bleed air branch pipe 320. The emergency pressure relief valve 410 is a normally open pressure relief valve. When the fluid pressure in the connecting branch pipe 420 exceeds the maximum set threshold, the pressure relief valve is activated to release the fluid in the connecting branch pipe 420, preventing damage to the bleed air system. The maximum set threshold is determined by those skilled in the art based on the actual aircraft engine type. The spare branch pipe 430 is connected to the second bleed air branch pipe 320. The detection box 440 is located on one side of the connecting branch pipe 420 and is used to detect the fluid pressure in the connecting branch pipe 420. The actual model of the detection box 440 can be selected according to actual needs. In this embodiment, a combination of fluid pressure and temperature instruments is used for detection. In other embodiments, the detection box 440 can be adjusted accordingly according to actual needs. The connecting branch pipe 420... It also includes a connecting regulating valve 421 and a first normally open manual regulating valve 422. The connecting regulating valve 421 is located on the connecting branch pipe 420 near the emergency relief valve 410, and the first normally open manual regulating valve 422 is located on the connecting branch pipe 420 away from the emergency relief valve 410. The first normally open manual regulating valve 422 is used to urgently disconnect the connection between the connecting branch pipe 420 and the bleed air system to prevent damage to the detection device from consequently damaging the aircraft engine's bleed air system, further protecting the aircraft engine's bleed air system. A spare branch pipe 421 is also included. 30 includes a backup regulating valve 431 and a second normally open manual regulating valve 432. The backup regulating valve 431 is located at the end of the backup branch pipe 430 near the second bleed branch pipe 320, and the second normally open manual regulating valve 432 is located at the end of the backup branch pipe 430 away from the second bleed branch pipe 320. The backup regulating valve 431 is used to adjust the fluid flow rate of the backup branch pipe 430 to adapt to the different stages of the bleed system. The second normally open manual regulating valve 432 is used to cut off the connection between the backup branch pipe 430 and the connecting branch pipe 420 in an emergency.

[0034] The first bleed branch pipe 310, the second bleed branch pipe 320, the connecting branch pipe 420 and the spare branch pipe 430 are all made of high-pressure resistant stainless steel to avoid corrosion by fluids containing moisture. They should be able to withstand at least 11 atmospheres of pressure to meet the testing requirements of the bleed system and to ensure that they will not rupture due to excessive pressure before the emergency pressure relief valve 410 releases air, thus preventing damage to personnel or equipment.

[0035] Working principle: Compressed air is supplied to the intake chamber 130 through the intake assembly 100 to meet the testing requirements of the bleed air system. A redundant air chamber 200 is set up to further store air, so as to avoid bleed air system failure due to malfunctions of the intake pump 110 or intake regulating valve 120 during bleed air intake. Nitrogen or cryogenic air can be supplied to the bleed air system through the second bleed air branch pipe 320 to enable various tests on the bleed air system, avoid frequent replacement and adjustment of the bleed air pipe, improve testing efficiency, and save time and labor costs. By setting up a relief branch pipe and an emergency pressure relief valve 410, damage to the bleed air system caused by excessive pressure during testing is prevented. A sealing cover 230 is set in the redundant air chamber 200 to facilitate the cleaning of dust and other impurities in the redundant air chamber 200, and to prevent the bleed air system from being affected by dust or impurities.

[0036] In the embodiments provided in this application, it should be understood that the disclosed apparatus and methods can be implemented in other ways. The apparatus embodiments described above are merely illustrative. For example, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. Furthermore, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Additionally, the displayed or discussed mutual couplings, direct couplings, or communication connections may be through some communication interfaces; indirect couplings or communication connections between devices or units may be electrical, mechanical, or other forms.

[0037] Finally, it should be noted that the above-described embodiments are merely specific implementations of the present invention, used to illustrate the technical solutions of the present invention, and not to limit it. The scope of protection of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any person skilled in the art can still modify or easily conceive of changes to the technical solutions described in the foregoing embodiments within the technical scope disclosed in the present invention, or make equivalent substitutions for some of the technical features; and these modifications, changes, or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A device for testing bleed air in aircraft engines, characterized in that, include: An intake assembly (100) includes an intake pump (110), an intake regulating valve (120), and an intake chamber (130). The intake pump (110) is located at one end of the intake assembly (100). One end of the intake regulating valve (120) is connected to the intake pump (110), and the other end is connected to the intake chamber (130). The intake chamber (130) includes a first bleed air inlet (131) and a first bleed air outlet (132). The first bleed air inlet (131) is connected to the intake regulating valve (120), and the first bleed air outlet (132) is located at one end of the side of the intake chamber (130). A redundant air chamber (200) includes an air inlet (210) and an air outlet (220), which are located at one end of the redundant air chamber (200). The air intake branch pipe (300) includes a first air intake branch pipe (310) and a second air intake branch pipe (320). One end of the first air intake branch pipe (310) is connected to a first air intake outlet (132) and the other end is connected to an air inlet (210). One end of the second air intake branch pipe (320) is connected to an air outlet (220). The detection terminal (400) includes an emergency pressure relief valve (410), a connecting branch pipe (420), a spare branch pipe (430), and a detection box (440). The connecting branch pipe (420) is connected to the second bleed branch pipe (320). The emergency pressure relief valve (410) is located on the connecting branch pipe (420) near one end of the second bleed branch pipe (320). The spare branch pipe (430) is connected to the second bleed branch pipe (320). The detection box (440) is located on one side of the connecting branch pipe (420) and is used to detect the fluid pressure inside the connecting branch pipe (420). The air intake chamber (130) also includes a pressure relief branch pipe (133), which is located at one end of the bottom of the air intake chamber (130). The pressure relief branch pipe (133) includes a pressure relief regulating valve (134), which is located at the end of the pressure relief branch pipe (133) away from the air intake chamber (130). One end of the first air intake branch pipe (310) is detachably connected to the first air intake outlet (132), and the first air intake branch pipe (310) is detachably connected to the air inlet (210); The redundant air chamber (200) also includes a sealing cover (230), which is located at the end of the redundant air chamber (200) where there is no air inlet (210) and air outlet (220); The second bleed air branch (320) also includes a second bleed air regulating valve (321) at the end near the detection terminal (400).

2. The apparatus for bleed air testing of an aircraft engine according to claim 1, characterized in that: A reflux shut-off valve (322) is provided at one end of the second air intake branch pipe (320) near the redundant air chamber (200).

3. The apparatus for bleed air testing of an aircraft engine according to claim 2, characterized in that: The backup branch pipe (430) includes a backup regulating valve (431) and a second normally open manual regulating valve (432). The backup regulating valve (431) is located at the end of the backup branch pipe (430) near the second bleed branch pipe (320), and the second normally open manual regulating valve (432) is located at the end of the backup branch pipe (430) away from the second bleed branch pipe (320).

4. The apparatus for bleed air testing of an aircraft engine according to claim 1, characterized in that: The connecting branch pipe (420) also includes a connecting regulating valve (421) and a first normally open manual regulating valve (422). The connecting regulating valve (421) is located on the connecting branch pipe (420) near the emergency relief valve (410), and the first normally open manual regulating valve (422) is located on the connecting branch pipe (420) away from the emergency relief valve (410).

5. The apparatus for bleed air testing of an aircraft engine according to claim 1, characterized in that: The first air intake branch (310) and the second air intake branch (320) are made of high-pressure resistant stainless steel.

6. The apparatus for bleed air testing of an aircraft engine according to claim 1, characterized in that: The connecting branch pipe (420) and the spare branch pipe (430) are made of high-pressure resistant stainless steel.

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