Engine of three-engine helicopter and air intake and exhaust arrangement structure of engine

Abstract

The invention belongs to the technical field of overall design of helicopters, and particularly relates to an engine of a three-engine helicopter and an intake and exhaust arrangement structure of the engine. The three engines are arranged in a delta shape; the two engines are arranged in front, are symmetrically arranged on two sides of the main speed reducer, and are respectively marked as a left engine and a right engine based on the heading direction; one engine is positioned on the right side of the rear part of the main speed reducer and is marked as a backward engine; the three engines are all used for feeding air forwards and exhausting air backwards; in the height direction, the backward engine is higher than the two front engines; and the backward engine air inlet channel extends forwards to the front part above the right engine.

Description

Technical Field

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[0001] The present invention belongs to the technical field of helicopter overall design, and particularly relates to an engine of a three-engine helicopter and its intake and exhaust layout configuration. Background Art

[0002] The power for a helicopter to hover and fly is provided by an engine. Conventional helicopters generally配备 one or two engines, and very few helicopters are equipped with three engines. Compared with single-engine or twin-engine helicopters, a three-engine configuration can provide a higher level of power redundancy. When one engine fails, the remaining two engines can still maintain sufficient power to ensure the safe return of the helicopter or the completion of a forced landing; in addition, a three-engine configuration can also provide more power for the helicopter in high-altitude areas, improving the mission capabilities in high-altitude areas. Compared with single-engine or twin-engine helicopters, a three-engine helicopter has safety and power advantages. However, the three-engine configuration layout is relatively complex, and the intake and exhaust of the three engines interfere with each other, affecting the engine intake efficiency, and further affecting the engine power and the performance of the whole aircraft. Due to the existence of the above problems, there are few现役 three-engine helicopters at present. Summary of the Invention

[0003] Object of the Invention: To propose an engine of a three-engine configuration helicopter and its intake and exhaust layout, which can reduce the risk of interference between the intake and exhaust of the engine, improve the engine intake efficiency, and enhance the flight performance and mission efficiency.

[0004] An embodiment of the present invention provides an engine of a three-engine helicopter and its intake and exhaust layout configuration, including: The three engines are arranged in a "pin" shape layout; Two engines are in the front, symmetrically arranged on both sides of the main reducer, and are respectively denoted as the left engine and the right engine based on the heading direction; One engine is located at the rear right of the main reducer, denoted as the rearward engine; All three engines have forward intake and rearward exhaust; In the height direction, the rearward engine is higher than the two forward engines; The intake duct of the rearward engine extends forward until the front part above the right engine.

[0005] Furthermore, The rear parts of the left engine and the right engine are outwardly deflected, with a 9-degree angle with the heading; There is a distance of 380 mm - 480 mm between the left engine and the right engine and the main reducer; The installation height of the rearward engine is 268 mm higher than that of the two forward engines.

[0006] Furthermore, It should be noted that there may be some inaccuracies in the translation due to the lack of clear context for some special terms. It is recommended to further optimize according to the actual situation. Also, the term "现役" is translated as "active service" here, which may need to be adjusted according to the specific context.The left engine air intake extends forward to the left, forming a fairing for the power compartment; the right engine air intake extends forward to the right, forming a fairing for the power compartment; the rear engine air intake moves forward, gradually increasing in height to the right side of the main reducer, above and in front of the right engine.

[0007] Furthermore, The left engine exhaust pipe extends approximately 930mm from the rear of the engine, curving slightly to the left to ensure that the exhaust tailflow does not affect the aircraft structure; the right engine exhaust pipe extends approximately 800mm from the rear of the engine, curving slightly to the right to ensure that the exhaust tailflow does not affect the aircraft structure; the rear-facing engine exhaust pipe extends approximately 1200mm from the rear of the engine, gradually curving to the right and rising upwards, with the final outlet located above the engine compartment, slightly to the right, to avoid the exhaust gas affecting the aircraft structure.

[0008] Furthermore, The left engine is connected to the main reducer 4 via the left engine power shaft, the left engine transition reducer, and the left main reducer power shaft in sequence. The right engine is connected to the main reducer 4 in sequence via the right engine power shaft, the right engine transition reducer, and the right main reducer power shaft; The rearward engine is connected to the main reducer 4 in sequence via the rearward engine power shaft, the rearward engine transition reducer, and the rearward main reducer power shaft.

[0009] Furthermore, The axis length of the left engine power shaft is 744mm, the axis length of the left engine transition reducer is 848mm, and it has an upward angle of 9.3 degrees with the horizontal line. The axis length of the left main reducer power shaft is 607mm.

[0010] Furthermore, The rearward engine power shaft has a length of 604mm, the rearward engine transition reducer has a length of 380mm and a downward angle of 20 degrees with the horizontal line, and the rearward main reducer has a length of 525mm.

[0011] In summary, the beneficial effects of the present invention are as follows: This invention, by rationally arranging the three engines and their intake and exhaust configurations, avoids mutual interference between the intake and exhaust of the three engines, effectively improving engine intake efficiency and enhancing flight performance and mission efficiency. Attached Figure Description

[0012] Figure 1 A top view of the power compartment (fairing perspective) provided for an embodiment of the present invention. Figure 2 A top view of the power compartment provided in an embodiment of the present invention; Figure 3 A left-side view of the engine compartment provided in an embodiment of the present invention; Figure 4 Right side view of the power cabin provided by an embodiment of the present invention; Figure 5 Schematic diagram of the left engine power transmission arrangement provided by an embodiment of the present invention; Figure 6 Schematic diagram of the right engine power transmission arrangement provided by an embodiment of the present invention; Figure 7 Schematic diagram of the rearward engine power output arrangement provided by an embodiment of the present invention. Detailed implementation manners

[0013] An embodiment of the present invention provides an engine and its intake and exhaust arrangement configuration for a three-engine helicopter, including: Three engines are arranged in a "pin" shape; Two engines are in the front, symmetrically arranged on both sides of the main reducer, and are respectively denoted as the left engine and the right engine based on the course direction; One engine is located on the right side at the rear of the main reducer, denoted as the rearward engine; All three engines have forward intake and rearward exhaust; In the height direction, the rearward engine is higher than the two front engines; The intake duct of the rearward engine extends forward until the front part above the right engine.

[0014] The rear parts of the left engine and the right engine are outwardly deflected, with an included angle of 9 degrees with the course; There is a distance of 380 mm - 480 mm between the left engine and the right engine and the main reducer; The installation height of the rearward engine is 268 mm higher than that of the two forward engines.

[0015] The intake duct of the left engine extends forward and leftward out of the power cabin fairing; the intake duct of the right engine extends forward and rightward out of the power cabin fairing; the intake duct of the rearward engine extends forward and gradually increases in height to the right side of the main reducer, in front of the right engine. [[ID=​​​​​The right engine is connected to the main reducer 4 through the right engine power shaft, the right engine transition reducer, and the right main reducer power shaft in sequence; The rear-facing engine is connected to the main reducer 4 through the rear-facing engine power shaft, the rear-facing engine transition reducer, and the rear-facing main reducer power shaft in sequence.

[0018] The axis of the left engine power shaft is 744 mm long, the axis of the left engine transition reducer is 848 mm long, with an upward angle of 9.3 degrees to the horizontal line, and the axis of the left main reducer power shaft is 607 mm long.

[0019] The axis of the rear-facing engine power shaft is 604 mm long, the axis of the rear-facing engine transition reducer is 380 mm long, with a downward angle of 20 degrees to the horizontal line, and the axis of the rear-facing main reducer power shaft is 525 mm long.

[0020] Embodiment: The present invention includes the arrangement of three engines and the intake and exhaust arrangements of the three engines.

[0021] The engine outputs power, and the power enters the transition reducer through the power shaft rotating at high speed. After the speed is reduced by the transition reducer, it enters the main reducer through the main reducer power shaft. The three engines have the same power transmission path.

[0022] Two engines are arranged on both sides of the main reducer, with the rear part flaring outwards, having an angle of 9 degrees with the course, and leaving a certain distance from the main reducer to留出空间 for maintenance on both sides of the main reducer; One engine is arranged on the right side at the rear of the main reducer.

[0023] To facilitate the arrangement of the intake duct of the rear-facing engine, the two front-facing engines and the rear-facing engine maintain a certain installation height difference in the height direction.

[0024] The intake duct of the front-facing left engine extends forward and left out of the power cabin fairing; the intake duct of the front-facing right engine extends forward and right out of the power cabin fairing; the intake duct of the rear-facing engine faces forward and gradually raises the height to the right side of the main reducer, in the front of the upper right side of the right engine.

[0025] The exhaust pipe of the front-facing left engine faces backward and is slightly bent to the left to ensure that the exhaust wake does not affect the airframe structure; the exhaust pipe of the front-facing right engine faces backward and is slightly bent to the right to ensure that the exhaust wake does not affect the airframe structure; the exhaust pipe of the rear-facing engine extends backward, gradually to the right and upward, and finally the outlet is above the power cabin, biased to the right, to avoid the exhaust gas of the exhaust pipe affecting the airframe structure.

[0026] The technical effects of the present invention: The technical advantages and functional effects compared with the prior art Technical advantages: The three engines are arranged in a "pin" shape layout, with two engines in the front (on both sides of the main reducer) and one engine (at the rear of the main reducer), all with forward intake and rearward exhaust.

[0027] In terms of height, the rear engine is higher than the two front engines, leaving space for the rear engine's air intake and facilitating rear engine air intake.

[0028] The rear-mounted engine air intake extends forward to the front of the right-side engine, ensuring that all engine air intakes are positioned to avoid the risk of rear-mounted engines drawing in exhaust gas from other engines. This effectively solves the problem of mutual interference between engine intakes and exhausts in a three-engine layout.

[0029] The main equipment and components that need to be installed in the power compartment of this invention include: Left engine 1a; Left engine drive shaft 1b Left engine transition reducer 1c Left main reduction power transmission 1d Left engine air intake 1e Left engine exhaust pipe 1f Left engine firewall 1g Rearward engine 2a; Rearward engine drive shaft 2b Rearward engine transition reducer 2c Rearward main reduction power transmission 2d Rearward engine air intake 2e Rearward engine exhaust pipe 2f Left engine firewall 2g Right-side engine 3a; Right engine drive shaft 3b Right-side engine transition reducer 3c Right-side main reduction power transmission 3d Right engine air intake 3e Right side engine exhaust pipe 3f Left engine firewall 3g Main reducer 4 like Figure 1 , 2 As shown in Figures 3 and 4, the engine layout is as follows: The left engine 1a is diagonally arranged to the left of the main reduction gearbox, and the right engine 3a is diagonally arranged to the right of the main reduction gearbox. The two engines are at a 9-degree angle to the heading and are kept at a certain distance from the main reduction gearbox (between 380mm and 480mm) to allow space for maintenance on both sides of the main reduction gearbox. The rearward-facing engine 2a is located on the right side of the rear of the main reduction gear. The rearward-facing engine 2a is 268mm higher than the two forward-facing engines 1a and 3a.

[0030] Air intake layout: The forward-facing left-side engine air intake 1e extends forward and to the left, intersecting with the engine compartment fairing 5a to form the left-side engine air intake 1e inlet. The forward-right engine air intake 3e extends forward and to the right, intersecting with the engine compartment cowling 5b to form the left engine air intake 3e inlet. The rearward engine air intake 2e moves forward and forward, gradually increasing in height to above the right engine, to the right of the main reducer 4, above the engine compartment fairing, forming the rear engine air intake inlet.

[0031] Engine exhaust layout: The engine exhaust pipe extends from the rear of the engine to the left (approximately 930mm in length), curving slightly to the left to ensure that the exhaust tailflow does not affect the left rear part of the engine body and other structures. The front right engine exhaust pipe extends from the rear of the engine to the rear (approximately 800mm in length), curving slightly to the right to ensure that the exhaust tailflow does not affect the right rear part of the engine body and other structures. The rear exhaust pipe 2e extends from the rear end 2a of the engine to the rear (approximately 1200mm in length), gradually moving to the right and rising upwards, with the final outlet located above the engine compartment, slightly to the right, to prevent the exhaust gas from the exhaust pipe 2g from affecting the rear right side of the engine body, tail beam, and other structures.

[0032] like Figure 5 , 6 As shown in Figure 7, the power output route is arranged as follows: The left engine 1a outputs power, which enters the transition reducer through the high-speed rotating power shaft 1b (axis 1h, 744mm long). After the speed is reduced by the transition reducer 1c (axis 1i, 848mm long, with an upward angle of 9.3 degrees to the horizontal line 1k), the power enters the main reducer through the main reduction power shaft 1d (axis 1j, 607mm long). All three engines have the same power transmission path.

[0033] The right-side engine is symmetrically arranged with the left-side engine.

[0034] The rear engine 2a outputs power, which enters the transition reducer through the high-speed rotating power shaft 2b (axis 2h, length 604mm). After the speed is reduced by the transition reducer 2c (axis 2i, length 380mm, with a downward 20-degree angle to the horizontal line 2k), the power enters the main reducer 4 through the main reducer power shaft 2d (axis 2j, length 525mm). All three engines have the same power transmission path.

Claims

1. An engine for a tri-copter and its intake and exhaust arrangement, characterized in that, Comprise: Three engines in "pin" shape layout; Two engines in front, symmetrically arranged on both sides of the main reducer, based on the heading direction, respectively recorded as left engine and right engine; One engine located at the right side of the main reducer rear, recorded as rear engine; Three engines are forward intake and rear exhaust; In the height direction, the rear engine is higher than the two front engines; The rear engine intake channel extends forward to the right side of the upper front of the right engine.

2. The engine and its intake and exhaust arrangement configuration of a three-engine helicopter according to claim 1, characterized in that, The left engine and the right engine have a 9-degree angle with the heading direction. The left engine and the right engine are 380-480mm away from the main reducer. The rear engine installation height is 268mm higher than the two front engines.

3. The engine and its intake and exhaust arrangement configuration of a three-engine helicopter according to claim 1, characterized in that, The left engine intake channel extends forward to the left side of the power cabin fairing; the right engine intake channel extends forward to the right side of the power cabin fairing; the rear engine intake channel extends forward and gradually increases in height to the right side of the main reducer, the front side above the right engine.

4. The engine and its intake and exhaust arrangement configuration of a three-engine helicopter according to claim 3, characterized in that, The left engine exhaust pipe extends backward from the rear end of the engine for about 930mm, slightly bends to the left, ensuring that the exhaust tail flow does not affect the aircraft structure; the right engine exhaust pipe extends backward from the rear end of the engine for about 800mm, slightly bends to the right, ensuring that the exhaust tail flow does not affect the aircraft structure; the rear engine exhaust pipe extends backward from the rear end of the engine for about 1200mm, gradually bends to the right and upward, and finally the outlet is above the power cabin, slightly to the right, avoiding the exhaust pipe tail gas affecting the aircraft structure.

5. The engine and its intake and exhaust arrangement configuration of a three-engine helicopter according to claim 4, characterized in that, The left engine is connected to the main reducer 4 through the left engine power shaft, the left engine transition reducer, and the left main reduction power shaft in turn; The right engine is connected to the main reducer 4 through the right engine power shaft, the right engine transition reducer, and the right main reduction power shaft in turn; The rear engine is connected to the main reducer 4 through the rear engine power shaft, the rear engine transition reducer, and the rear main reduction power shaft in turn.

6. The engine and its intake and exhaust arrangement configuration of a three-engine helicopter according to claim 5, characterized in that, The axis of the left engine power shaft is 744mm long, the axis of the left engine transition reducer is 848mm long and has a 9.3-degree upward angle with the horizontal line, and the axis of the left main reduction power shaft is 607mm long.

7. The engine and its intake and exhaust arrangement configuration of a three-engine helicopter according to claim 5, characterized in that, The axis of the rear engine power shaft is 604mm long, the axis of the rear engine transition reducer is 380mm long and has a 20-degree downward angle with the horizontal line, and the axis of the rear main reduction power shaft is 525mm long.

8. A helicopter characterized by The helicopter has an engine and its intake and exhaust arrangement configuration of a three-engine helicopter as claimed in any of claims 1-7.

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