CN214608102U

CN214608102U - Rectification wrapping device of turboprop engine

Info

Publication number: CN214608102U
Application number: CN202023239510.4U
Authority: CN
Inventors: 李志强; 张红苗; 李丁
Original assignee: Avic Shijiazhuang Aircraft Industry Group Corp ltd
Current assignee: Avic Shijiazhuang Aircraft Industry Group Corp ltd
Priority date: 2020-12-29
Filing date: 2020-12-29
Publication date: 2021-11-05
Anticipated expiration: 2030-12-29

Abstract

The utility model 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 connected in turn 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 utility model discloses a connect and connect through the fast-release lock pin through the lapped mode that sinks between each radome fairing, the radome fairing also adopts the fast-release lock pin to be connected with starting the frame simultaneously, can effectually prevent that each radome fairing from droing, it has engine passenger cabin ventilation inspection socket to open simultaneously on the radome fairing down, the oil cooling mouth, the motor cooling mouth, the GPU inspection socket, can be when not tearing down the engine radome fairing can be to the passenger cabin ventilation unit of engine, the cold device that lacks of oil, the motor cooling unit, the GPU of engine is examined.

Description

Rectification wrapping device of turboprop engine

Technical Field

The utility model relates to a rectification foreskin device of 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 existing engine rectifying wrapper is easy to fall off when being connected with an engine frame.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that a better turboprop engine's of anti-drop and maintainability rectification foreskin device is provided.

The utility model adopts the technical proposal that: 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 utility model discloses an actively the effect does: the utility model discloses a connect and connect through the fast-release lock pin through the lapped mode that sinks between each radome fairing, the radome fairing also adopts the fast-release lock pin to be connected with starting the frame simultaneously, can effectually prevent that each radome fairing from droing.

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 structural view of the left fairing of the present invention;

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

FIG. 4 is a schematic view of the right middle fairing of the present invention;

fig. 5 is a schematic structural view of the oil cooling port of the present invention.

Detailed Description

As shown in the attached drawings 1-5, the utility model comprises an upper fairing 1, a right fairing, a lower fairing 7 and a left fairing which are connected in turn from left to right, wherein the upper fairing, the right fairing, the lower fairing and the left fairing form an approximate cone shape, and the fairings are fixed together with an engine frame through a quick-release lock pin 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, the utility model discloses an inside is equipped with prevents hot wall, divide into equipment cabin and engine compartment with its inside.

The utility model discloses can effectively prevent the interference of air foreign objects such as rain, snow, hail, guarantee the normal operating of engine to there is good protection effect to the equipment of aircraft. 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.

Claims

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).