阅读说明：本技术 一种涡桨发动机的整流包皮装置 (Rectification wrapping device of turboprop engine ) 是由 李志强 张红苗 李丁 于 2020-12-29 设计创作，主要内容包括：本发明涉及一种涡桨发动机的整流包皮装置,包括左右依次连接形成近似圆锥状的上整流罩、右整流罩、下整流罩以及左整流罩,各整流罩之间通过下陷搭接的方式通过快卸锁钉与发动机架固定到一起；本发明的各个整流罩之间通过下陷搭接的方式连接且通过快卸锁钉连接,同时整流罩与发动机架也采用快卸锁钉进行连接,能有效的防止各整流罩脱落,同时在下整流罩上开有发动机座舱通风检查口、油冷却口、电机冷却口、GPU检查口,能在不拆下发动机整流罩的同时可以对发动机的座舱通风装置、油冷缺装置、电机冷却装置、发动机的GPU进行检查。(The invention relates to a fairing device of a turboprop engine, which comprises an upper fairing, a right fairing, a lower fairing and a left fairing which are sequentially connected from left to right to form an approximate cone shape, wherein the fairings are fixed with an engine frame through quick-release lock pins in a sinking lap joint mode; the engine cowlings are connected in a sunken lap joint mode and are connected through the quick-release lock nails, meanwhile, the cowlings are connected with the engine frame through the quick-release lock nails, the cowlings can be effectively prevented from falling off, meanwhile, the lower cowling is provided with the engine cabin ventilation inspection port, the oil cooling port, the motor cooling port and the GPU inspection port, and the engine cabin ventilation device, the oil cooling device, the motor cooling device and the GPU of the engine can be inspected while the engine cowlings are not detached.)

1. A fairing device of a turboprop engine is characterized by comprising an upper fairing (1), a right fairing, a lower fairing (7) and a left fairing which are sequentially connected from left to right to form an approximate cone shape, wherein the fairings are fixed with an engine frame through quick-release lock pins in a sinking lap joint mode.

2. The fairing device of the turboprop engine according to claim 1, characterized in that the right fairing includes a right middle fairing (2), a right front fairing (3) and a right rear fairing (4), the right front fairing (3), the right middle fairing (2) and the right rear fairing (4) are connected in sequence from front to back and the left and right ends are connected with the upper fairing (1) and the lower fairing (7).

3. The fairing device of the turboprop according to claim 1 or 2, characterized in that said left fairing comprises a left front fairing (5) and a left rear fairing (6) connected to the lower side of the left front fairing (5), and the two ends of the left front fairing (5) and the left rear fairing (6) are respectively connected to the lower fairing (7) and the upper fairing (1).

4. The fairing device of the turboprop engine according to claim 3, characterized in that the lower fairing (7) is provided with an engine cabin ventilation inspection port (11), an oil cooling port (9), a motor cooling port (8) and a GPU inspection port (10), the left front fairing (5) is provided with a lubricating oil tank inspection door (12) and a generator inspection door (13), and the right middle fairing (2) is provided with an exhaust pipe sealing plate (14).

5. The fairing device of claim 2, wherein adjacent fairings are connected by a quick release staple.

6. The fairing device of the turboprop according to claim 4, characterized in that the engine compartment ventilation inspection opening (11), the oil cooling opening (9), and the motor cooling opening (8) each comprise a groove (15) provided in the lower fairing (7), an inspection opening (16) provided in the groove (15), and a baffle above the inspection opening (16), the baffle being flush with the lower fairing (7).

Technical Field

The invention relates to a rectifying wrapper device of a turboprop engine.

Background

A small-sized general-purpose airplane adopting a turboprop engine needs to be provided with a fairing so as to ensure that the engine can prevent the interference of foreign objects in the air such as rain, snow, hail and the like. The normal operation of the engine is ensured, and the aircraft equipment is well protected.

The rectifying wrapper is also characterized in that the rectifying wrapper has a streamline shape, has good aerodynamic parameters and can reduce air resistance for an engine. The engine fairing and the frame 1 have a clearance of about 5mm, so that the impact of the engine fairing on the frame 1 caused by the vibration of the engine frame in the process of landing and landing of an airplane can be effectively prevented.

The existing engine rectifying wrapper is easy to fall off when being connected with an engine frame.

Disclosure of Invention

The technical problem to be solved by the invention is to provide a rectifying and wrapping device of a turboprop engine, which is anti-falling and has better maintainability.

The technical scheme adopted by the invention is as follows: a fairing device of a turboprop engine comprises an upper fairing, a right fairing, a lower fairing and a left fairing which are sequentially connected from left to right to form an approximate cone shape, wherein the fairings are fixed with an engine frame through quick-release lock pins in a sinking lap joint mode.

Further, the right fairing comprises a right middle fairing, a right front fairing and a right rear fairing, wherein the right front fairing, the right middle fairing and the right rear fairing are sequentially connected from front to back, and the left end and the right end of the right front fairing are connected with the upper fairing and the lower fairing.

Furthermore, the left fairing comprises a left front fairing and a left rear fairing connected to the lower side of the left front fairing, and the two ends of the left front fairing and the left rear fairing are respectively connected with the lower fairing and the upper fairing.

Furthermore, an engine cabin ventilation inspection port, an oil cooling port, a motor cooling port and a GPU inspection port are formed in the lower fairing, a sliding oil tank inspection door and a generator inspection door are formed in the left front fairing, and an exhaust pipe sealing plate is arranged on the right middle fairing.

Furthermore, two adjacent cowlings are connected through quick-release lock pins.

Furthermore, the engine cabin ventilation inspection port, the oil cooling port and the motor cooling port all comprise a groove arranged on the lower fairing, an inspection port arranged on the groove and a baffle positioned above the inspection port, and the baffle is flush with the lower fairing.

The invention has the positive effects that: the cowlings are connected in a sunken lap joint mode and connected through the quick-release lock pins, and meanwhile, the cowlings and the engine frame are connected through the quick-release lock pins, so that the cowlings can be effectively prevented from falling off.

Meanwhile, an engine cabin ventilation inspection port, an oil cooling port, a motor cooling port and a GPU inspection port are formed in the lower fairing, and the engine cabin ventilation device, the oil cooling device, the motor cooling device and the GPU of the engine can be inspected while the engine fairing is not detached.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic view of the left fairing of the present invention;

FIG. 3 is a schematic view of a lower fairing of the present invention;

FIG. 4 is a schematic view of the right mid-fairing configuration of the present invention;

FIG. 5 is a schematic view showing the structure of an oil cooling port of the present invention.

Detailed Description

As shown in attached figures 1-5, the engine comprises an upper fairing 1, a right fairing, a lower fairing 7 and a left fairing which are sequentially connected from left to right, wherein the upper fairing, the lower fairing, the left fairing, the right fairing, the left fairing and the right fairing form an approximate cone shape, and the fairings are fixed together with an engine frame through quick-release lock pins in a sinking lap joint mode.

And the right fairing comprises a right front fairing 3, a right middle fairing 2 and a right rear fairing 4 which are sequentially connected from front to back, and the left and right ends of the right front fairing 3, the right middle fairing 2 and the right rear fairing 4 are respectively connected with the upper fairing 1 and the lower fairing 7. The left fairing comprises a left front fairing 5 and a left rear fairing 6 connected to the lower side of the left front fairing 5, and the two ends of the left front fairing 5 and the left rear fairing 6 are respectively connected with a lower fairing 7 and an upper fairing 1. Each fairing is made of composite materials, is light in weight and high in strength, and can completely bear airflow impact generated by the speed of a small airplane.

The adjacent upper fairing 1, right front fairing 3, right middle fairing 2, right rear fairing 4, lower fairing 7, left front fairing 5 and left rear fairing 6 are connected by means of sinking lap joint. In detail, a connecting plate which is concave inwards is designed at one edge of two adjacent cowlings, and the other cowling is overlapped on the connecting plate and then connected by using a quick-release locking nail.

The lower cowling 7 is provided with an engine cabin ventilation inspection port 11, an oil cooling port 9, a motor cooling port 8, and a GPU inspection port 10, and the engine cabin ventilation device, the oil cooling device, the motor cooling device, and the GPU of the engine can be inspected without removing the engine cowling.

The left front fairing 5 is provided with a lubricating oil tank inspection door 12 and a generator inspection door 13, and the lubricating oil amount of the airplane belongs to the inspection subject before flight, so that the lubricating oil amount can be conveniently inspected by the lubricating oil tank inspection door 12. The fairing 2 is provided with an exhaust pipe sealing plate 14 which can play a role in sealing exhaust pipe tail gas.

Preferably, the engine compartment ventilation inspection port 11, the oil cooling port 9 and the motor cooling port 8 each include a groove 15 provided in the lower cowl 7, an inspection port 16 provided in the groove 15, and a baffle located above the inspection port 16, the baffle being flush with the lower cowl 7.

Preferably, a firewall is arranged inside the engine room, and the inside of the engine room is divided into an equipment room and an engine room.

The invention can effectively prevent the interference of foreign objects in the air such as rain, snow, hail and the like, ensure the normal operation of the engine and have good protection effect on the equipment of the airplane. The aircraft has good aerodynamic appearance, effectively reduces the influence of aerodynamic force on the flight, has excellent maintainability, can greatly reduce the cost of the aircraft, and is suitable for being applied to small turboprop aircrafts, in particular to Y5B aircrafts.