Aero-engine hydrogen energy test building

Abstract

The utility model discloses an aero-engine hydrogen energy test run plant, including air intake tower, test run room, exhaust tower, the air intake tower is communicated with one end of test run room, and the other end of test run room is communicated with exhaust tower through exhaust system, the exhaust mechanism is equipped with in the one end of exhaust tower of test run room top near, exhaust mechanism includes wall hole, remote control door and fan, the wall hole is located test run room near exhaust tower one side top, the remote control door of wall hole installation adjusts the wall hole opening, the fan is located in the inside of roof of test run room, and the fan air outlet faces wall hole. The utility model discloses through being located in the design of exhaust mechanism of test run room top, can emit the hydrogen of leakage fast unobstructed from test run room, and timely and effectively eliminates the security risk.

Description

Technical Field

[0001] This utility model relates to the field of aircraft engine testing, specifically to an aircraft engine hydrogen energy testing facility. Background Technology

[0002] Aero engines are highly complex and precise thermodynamic machines, and ground tests of complete aero engines are generally conducted in dedicated test facilities. Currently, environmentally friendly, pollution-free, and zero-carbon emission hydrogen-powered aero engines are gradually gaining public attention. Based on the "Safety Regulations for Hydrogen-Oxygen Rocket Engine Test Systems" (QJ10013-2008) and the experience in constructing hydrogen fuel engine test stands in the aerospace field, hydrogen-powered aero engine test stands differ significantly from traditional indoor aero engine test stands in terms of safety considerations for hydrogen fuel use.

[0003] Traditional turboshaft engine test facilities, powered by fuel, typically employ a "U"-shaped layout, consisting of a vertical air intake, a horizontal test chamber, and a vertical exhaust duct. Clean airflow enters the test chamber through the vertical air intake, is inhaled and combusted by the test engine, and then the combustion products are discharged through the vertical exhaust duct. However, using traditional turboshaft engine test facilities for hydrogen-powered aero-engine testing presents several drawbacks:

[0004] 1. Hydrogen is lighter than air and is extremely prone to leakage. During the experiment, it may leak from the test system and accumulate at the top of the test chamber, posing an explosion hazard.

[0005] 2. The fuel room and control room are adjacent to the test workshop, posing a significant safety hazard.

[0006] If the test area is completely open, there will also be several drawbacks:

[0007] 1. The test noise is as high as 110dB(A) to 130dB(A). The fully open test area means that the noise can only be attenuated naturally. To meet the site noise requirements, a very large area is required.

[0008] 2. The open nature of the test area makes the test more susceptible to the influence of climate and weather factors, such as sustained low temperatures and thunderstorms, which may affect the test results.

[0009] 3. The unprotected testing equipment is susceptible to wind and sun exposure, which accelerates aging and corrosion, increasing maintenance costs in the later stages. Summary of the Invention

[0010] The present invention aims to provide a hydrogen energy test facility for aircraft engines, which can avoid hydrogen accumulation on the top of the test facility and eliminate safety hazards.

[0011] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0012] A hydrogen energy test facility for an aircraft engine includes an air intake tower, a test workshop, and an exhaust tower; the air intake tower is connected to one end of the test workshop, and the other end of the test workshop is connected to the exhaust tower through an exhaust system; its structural feature is that an exhaust mechanism is provided at the end of the top of the test workshop near the exhaust tower.

[0013] The exhaust mechanism includes a wall opening, a remote-controlled door, and a fan. The wall opening is located above the side of the test workshop near the exhaust tower. The wall opening is equipped with a remote-controlled door for adjusting the opening degree. The fan is located inside the roof of the test workshop, and the fan outlet faces the wall opening.

[0014] During the test run of a hydrogen-powered aircraft engine, the leaked hydrogen gas rose to near the roof of the test workshop. Then, accelerated by the fan, it left the test workshop through an opening in the wall, preventing the accumulation of hydrogen gas on the roof and eliminating safety hazards.

[0015] Based on the embodiments of this utility model, further optimizations can be made to this utility model. The optimized technical solutions are as follows:

[0016] In one preferred embodiment, the exhaust system is located below the exhaust tower on the side of the test workshop, and discharges the combustion products generated by the test engine in the test workshop to the exhaust tower and out of the test workshop building.

[0017] In one preferred embodiment, a canopy is installed above the wall opening, located on the roof side near the exhaust tower, to prevent rainwater from entering the test workshop through the wall opening. Furthermore, the canopy forms a continuous slope from the side of the test workshop near the air intake tower towards the side near the exhaust tower, with the fan located at the starting end of the slope. This inclined design enhances the fan's exhaust effect and improves ventilation efficiency.

[0018] In one preferred embodiment, the fan is an explosion-proof axial flow fan. Explosion-proof axial flow fans have explosion-proof characteristics and can operate safely in environments containing flammable and explosive gases such as hydrogen.

[0019] In one preferred embodiment, the roof of the test chamber is made of lightweight explosion-proof roof, which ensures that the test chamber can quickly release explosive energy during the explosion.

[0020] In one preferred embodiment, the test chamber adopts a reinforced concrete explosion-proof structure, which can ensure that the main body of the test chamber can maintain stability after the explosion is vented.

[0021] The design of the hydrogen energy aero-engine test facility of this utility model can be used for ground test bench testing of the entire hydrogen energy aero-engine, avoiding hydrogen accumulation on the top of the test facility and eliminating safety hazards.

[0022] Compared with the prior art, the beneficial effects of this utility model are:

[0023] 1. This utility model can accommodate both conventional energy aero-engine testing and hydrogen energy aero-engine testing;

[0024] 2. By installing an exhaust mechanism at the top of the test chamber, this utility model enables leaked hydrogen to leave the test chamber quickly and without obstruction, thus eliminating safety hazards.

[0025] 3. The wall opening of the test chamber of this utility model can be adjusted to reduce the impact of external factors on the test equipment in the test chamber, and at the same time reduce the impact of test noise on the outside world. Attached Figure Description

[0026] Figure 1 This is a structural diagram of a hydrogen-powered test facility for aircraft engines.

[0027] Figure 2 yes Figure 1 The view along direction A.

[0028] In the diagram:

[0029] 1-Intake tower, 2-Test workshop, 3-Exhaust tower, 4-Roof, 5-Wall opening, 6-Remote control door, 7-Canopy, 8-Fan, 9-Main airflow, 10-Exhaust system, 11-Test engine, 12-Fuel room, 13-Process equipment room, 14-Preparation room, 15-Process preparation room, 16-Equipment room, 17-Lubricating oil room, 18-Waiting room for testing, 19-Power distribution room, 20-Spare parts room, 21-Fitter's room, 22-Operating room. Detailed Implementation

[0030] The present invention will be described in detail below with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in the embodiments of the present invention can be combined with each other. For ease of description, the terms "upper," "lower," "left," and "right" appearing below only indicate that they correspond to the upper, lower, left, and right directions in the accompanying drawings and do not limit the structure.

[0031] Please see Figures 1-2As shown, this embodiment provides a hydrogen energy test facility for an aero-engine, including an intake tower 1, a test workshop 2, an exhaust tower 3, a roof 4, wall openings 5, a remote-controlled door 6, a canopy 7, a fan 8, a main airflow system 9, and an exhaust system 10. The test workshop 2 houses a test engine 11. The entire test workshop 2 includes a process equipment room 13, a preparation room 14, a process preparation room 15, an equipment room 16, a lubricating oil room 17, a waiting-for-test room 18, a power distribution room 19, a spare parts room 20, and a fitter's room 21. A fuel room 12 and an operating room 22 are located on opposite sides of the test workshop 2, thus separating the fuel room 12 and the operating room 22 from the main body of the test workshop 2. The distances between the fuel room 12 and the operating room 22, as well as their distances from the test workshop 2, are determined according to the requirements of the "Safety Regulations for Hydrogen-Oxygen Rocket Engine Test Systems" (QJ10013-2008).

[0032] The intake tower 1 is connected to one end of the test workshop 2, and the other end of the test workshop 2 is connected to the exhaust tower 3 via the exhaust system 10. An exhaust mechanism is located at the top of the test workshop 2 near the exhaust tower 3. The exhaust mechanism includes a wall opening 5, a remote-controlled door 6, and a fan 8. The wall opening 5 is located above the side of the test workshop 2 near the exhaust tower 3, and the wall opening 5 is equipped with a remote-controlled door 6 for adjusting its opening. The fan 8 is located inside the roof 4 of the test workshop 2, with its outlet facing the wall opening 5. The exhaust system 10 is located below the side of the test workshop 2 near the exhaust tower 3. A canopy 7 is installed above the wall opening 5, located on the side of the roof 4 near the exhaust tower 3. The canopy 7 forms a continuous slope from the side of the test workshop 2 near the intake tower 1 to the side near the exhaust tower 3, with the fan 8 located at the starting end of the slope of the canopy 7. The roof 4 of the test workshop 2 is a lightweight explosion-proof roof, and the main structure of the test workshop 2 and the fuel room 12 are both constructed of reinforced concrete explosion-proof structures.

[0033] This invention can accommodate both conventional energy aircraft engine testing and hydrogen energy aircraft engine testing. The operating mode of this invention is as follows:

[0034] During the conventional energy test, the main airflow 9 enters the test workshop 2 through the intake tower 1. After being drawn in and burned by the test engine 11 in the test workshop 2, the combustion products water or water vapor produced by the engine are discharged into the exhaust tower 3 through the exhaust system 10 and discharged through the outlet of the exhaust tower 3. Throughout the process, the remote control door 6 is not opened, the wall hole 5 remains closed, and the fan 8 does not work.

[0035] During the hydrogen-powered aero-engine test, the main airflow path remained consistent with conventional tests. The main airflow 9 entered the test workshop 2 through the intake tower 1. Inside the test workshop 2, it was drawn in and combusted by the test engine 11. The combustion products, water or water vapor, were discharged through the exhaust system 10 into the exhaust tower 3 and then exited through the exhaust tower 3 outlet. Simultaneously, the remote-controlled door 6 opened, and the fan 8 operated. The leaked hydrogen rose to the vicinity of the roof 4 of the test workshop 2. Then, accelerated by the fan 8, it moved along the roof 4 of the test workshop 2 towards the wall opening 5 on the side of the test workshop 2 closest to the exhaust tower 3, and exited the test workshop 2 through the wall opening 5 after the remote-controlled door 6 opened. At this point, the hydrogen did not accumulate on the top of the test workshop 2, eliminating the risk of explosion.

[0036] The above embodiments should be understood as being used only to illustrate the present invention more clearly, and not to limit the scope of the present invention. After reading the present invention, any modifications of the embodiments by those skilled in the art in various equivalent forms fall within the scope defined by the appended claims.

Claims

1. A hydrogen energy test facility for an aircraft engine, comprising an air intake tower (1), a test workshop (2), and an exhaust tower (3); wherein one end of the air intake tower (1) is connected to one end of the test workshop (2), and the other end of the test workshop (2) is connected to the exhaust tower (3) via an exhaust system (10); characterized in that: The test workshop (2) has an exhaust mechanism at one end of its top near the exhaust tower (3); The exhaust mechanism includes a wall opening (5), a remote control door (6), and a fan (8). The wall opening (5) is located above the side of the test workshop (2) near the exhaust tower (3). The wall opening (5) is equipped with a remote control door (6) for adjusting the opening of the wall opening (5). The fan (8) is located inside the roof (4) of the test workshop (2), and the air outlet of the fan (8) faces the wall opening (5).

2. The hydrogen energy test facility for aero-engines according to claim 1, characterized in that: The exhaust system (10) is located below the test workshop (2) on the side near the exhaust tower (3).

3. The hydrogen energy test facility for aero-engines according to claim 1, characterized in that: A canopy (7) is installed above the wall opening (5), and the canopy (7) is located on the side of the roof (4) near the exhaust tower (3).

4. The hydrogen energy test facility for aero-engines according to claim 3, characterized in that: The canopy (7) forms a continuous slope from low to high on the side of the test workshop (2) near the air intake tower (1) to the side near the exhaust tower (3), and the fan (8) is located at the starting end of the slope of the canopy (7).

5. The aircraft engine hydrogen energy test facility according to any one of claims 1-4, characterized in that: The fan (8) is an explosion-proof axial flow fan.

6. The hydrogen energy test facility for aero-engines according to any one of claims 1-4, characterized in that: The roof (4) is made of lightweight explosion-proof material.

7. The hydrogen energy test facility for aero-engines according to any one of claims 1-4, characterized in that: The test workshop (2) adopts a reinforced concrete explosion-proof structure.

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