CN211592908U

CN211592908U - Autorotation rotorcraft engine hood

Info

Publication number: CN211592908U
Application number: CN202020213687.8U
Authority: CN
Inventors: 宋梓涵; 张江涛; 王一龙
Original assignee: Hebei Tianqi Tongyu Aviation Equipment Technology Development Co ltd
Current assignee: Hebei Tianqi Tongyu Aviation Equipment Technology Development Co ltd
Priority date: 2020-02-26
Filing date: 2020-02-26
Publication date: 2020-09-29
Anticipated expiration: 2030-02-26

Abstract

The utility model discloses a rotation gyroplane engine cover, including cabin, fastening bolt, engine bonnet, engine and vent. The engine cover is in streamline transition with the top of the engine cabin, the function of separating the pre-rotation flexible shaft and the engine is achieved, the size of an engine fairing is reduced as much as possible, two ventilation openings are formed in the ventilation openings, the ventilation openings are respectively located on two sides of the engine cover, the engine has a better cooling effect under the action of airflow, the performance of the engine under the high-temperature and high-humidity environment is improved, the service life of the engine is prolonged, the engine cover is made of composite materials, the weight is light, the effective load of the aircraft can be increased, the maneuverability of the aircraft is improved, four groups of fastening bolts are arranged, the front end of the engine cover is detachably connected with the engine cabin through the fastening bolts, the rear end of the engine cover is connected with the engine through a supporting piece, the firmness of installation of the engine cover is improved, meanwhile.

Description

Autorotation rotorcraft engine hood

Technical Field

The utility model relates to a aircraft bonnet specifically is a rotation gyroplane engine bonnet, belongs to gyroplane technical field.

Background

Autogyroplanes, known in English as Autogyro (from Greek α upsilon tau)

+γ

ρο

Self-rotating), also known as Gyroplane, rotorcraft or rotorcraft (Gyrocopter), which is a rotorcraft that is driven by the rotor spinning rather than power to obtain lift, generally with a propulsive propeller to provide forward power, in this respect, similar to a fixed wing aircraft, and the engine mechanism of which plays an important role in it, the cowls of which are therefore also of increasing interest.

Although the existing autorotation rotorcraft engine hood is widely used, the existing autorotation rotorcraft engine hood still has some problems in the actual use process, firstly, most of the existing autorotation rotorcraft engine hoods can only play the role of isolation, the normal working environment of the engine can not be ensured, secondly, some lifting spaces exist in the radiating aspect of the existing autorotation rotorcraft engine, the effective and rapid heat radiation can not be carried out, thirdly, the existing autorotation rotorcraft engine hood can generate certain troubles in the installation and disassembly processes, the steps are complex, and the thick weight of the hood affects the working efficiency and the maneuverability.

SUMMERY OF THE UTILITY MODEL

An object of the present invention is to provide a rotary rotorcraft engine cover for solving the above problems.

The utility model discloses a following technical scheme realizes above-mentioned purpose: a self-rotating rotorcraft engine cover comprises a cabin, fastening bolts, an engine cover, an engine and a ventilation opening; the engine cover is connected with the engine room through a fastening bolt, the engine cover is clamped above the engine, the engine is installed in the engine room, and a ventilation opening is formed in the engine cover.

Preferably, in order to separate the pre-rotation flexible shaft from the engine and reduce the size of the engine fairing as much as possible, the engine fairing is in flow linear transition with the top of the cabin.

Preferably, in order to improve the performance of the engine in a high-temperature and high-humidity environment and prolong the service life of the engine, two air vents are formed and are respectively positioned on two sides of the engine cover.

Preferably, the engine cover is made of composite materials in order to increase the effective load of the airplane and improve the maneuverability of the airplane.

Preferably, in order to improve the firmness of the installation of the engine cover and facilitate the cleaning or maintenance of the engine, the four groups of fastening bolts are arranged, the front end of the engine cover is detachably connected with the engine room through the fastening bolts, and the rear end of the engine cover is connected with the engine through the supporting piece.

The utility model has the advantages that: the self-rotating rotorcraft engine cover has reasonable design, and the engine cover and the top of the engine cabin are in streamline transition, thereby playing the role of separating the pre-rotating flexible shaft and the engine, the size of the engine fairing is reduced as much as possible, two air vents are arranged and are respectively positioned at two sides of the engine hood, so that the engine has better cooling effect under the action of airflow, thereby improving the performance of the engine under the high-temperature and high-humidity environment and prolonging the service life of the engine, the engine cover is made of composite materials, the weight is light, can increase the effective load of the airplane and improve the maneuverability of the airplane, four groups of fastening bolts are arranged, and the engine bonnet front end is detachable with the cabin through fastening bolt and is connected, and the engine bonnet rear end is connected with the engine through support piece, improves the fastness of engine bonnet installation, also convenient to detach simultaneously to wash or maintain the engine.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

In the figure: 1. cabin, 2, fastening bolt, 3, engine cover, 4, engine and 5, and ventilation opening.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1, a rotary wing aircraft engine cover includes a nacelle 1, a fastening bolt 2, an engine cover 3, an engine 4, and a vent 5; the engine cover 3 is connected with the engine room 1 through a fastening bolt 2, the engine cover 3 is clamped above an engine 4, the engine 4 is installed in the engine room 1, and a ventilation opening 5 is formed in the engine cover 3.

The engine cover 3 and the top of the engine room 1 are in flow linear transition, which plays a role of separating the pre-rotation flexible shaft and the engine, the size of the engine fairing is reduced as much as possible, two air vents 5 are arranged and are respectively positioned at two sides of the engine hood 3, so that the engine has better cooling effect under the action of airflow, thereby improving the performance of the engine under the high-temperature and high-humidity environment and prolonging the service life of the engine, the engine cover 3 is made of composite materials, has light weight, the effective load of the airplane can be increased, the maneuverability of the airplane can be improved, four groups of fastening bolts 2 are arranged, and 3 front ends of engine bonnet are detachable connection through fastening bolt 2 and cabin 1, and 3 rear ends of engine bonnet are connected with engine 4 through support piece, improve the fastness of 3 installations of engine bonnet, also convenient to detach simultaneously to wash or maintain engine 4.

The working principle is as follows: when the autorotation rotorcraft engine hood is used, the engine hood 3 plays a role in separating a prewhirl flexible shaft from an engine, the size of an engine fairing is reduced as far as possible under the condition of ensuring the streamline transition with the top of a cabin 1, and the design of the ventilation openings 5 on two sides ensures that the engine 4 has a better cooling effect under the action of airflow, so that the performance of the engine 4 in a high-temperature and high-humidity environment is improved, the service life of the engine is prolonged, meanwhile, the engine hood 4 is made of composite materials and has a smaller size, so that the weight is light, the effective load of an airplane can be increased, and the maneuverability of the airplane is improved.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides a rotation gyroplane engine bonnet which characterized in that: comprises a cabin (1), a fastening bolt (2), an engine cover (3), an engine (4) and a ventilation opening (5); the engine cover (3) is connected with the engine room (1) through a fastening bolt (2), the engine cover (3) is clamped above the engine (4), the engine (4) is installed in the engine room (1), and the engine cover (3) is provided with a ventilation opening (5).

2. The rotorcraft engine cover of claim 1, wherein: the engine cover (3) and the top of the engine room (1) are in streamline transition.

3. The rotorcraft engine cover of claim 1, wherein: two air vents (5) are formed and are respectively positioned on two sides of the engine cover (3).

4. The rotorcraft engine cover of claim 1, wherein: the engine cover (3) is made of composite materials.

5. The rotorcraft engine cover of claim 1, wherein: the fastening bolts (2) are arranged in four groups, the front end of the engine cover (3) is detachably connected with the engine room (1) through the fastening bolts (2), and the rear end of the engine cover (3) is connected with the engine (4) through the supporting piece.