阅读说明：本技术 一种发动机舱液压油放油装置 (Engine compartment hydraulic oil discharging device ) 是由 韩学剑 刘学 吕伯杰 佟逸辉 张晟昊 于 2019-09-30 设计创作，主要内容包括：本发明公开了一种发动机舱液压油放油装置,包括：螺纹旋进套和顶芯；螺纹旋进套中心设置阶梯形螺纹通孔；顶芯为设有外螺纹的筒状结构,其一端设置有定位轴肩；顶芯的外径与螺纹旋进套的阶梯形螺纹通孔孔径较小端一致,顶芯同轴套装在螺纹旋进套的阶梯形螺纹通孔内,并与螺纹旋进套孔径较小端螺纹连接；顶芯的定位轴肩抵触螺纹旋进套的阶梯形螺纹通孔的台阶面；顶芯定位轴肩所在端端面与螺纹旋进套的阶梯形螺纹通孔的大端端面之间预留设定距离；顶芯中心开设通孔,其轴肩所在端的通孔内设置凸台,凸台的另一端伸出顶芯轴肩所在端设定长度,用于与飞机上的弹性自封活门的阀芯对顶,进而打开飞机上的弹性自封活门,使液压油进入顶芯的通孔中。(The invention discloses an engine compartment hydraulic oil discharging device, which comprises: a thread screw-in sleeve and a top core; the center of the thread screwing sleeve is provided with a stepped thread through hole; the top core is a cylindrical structure provided with external threads, and one end of the top core is provided with a positioning shaft shoulder; the outer diameter of the top core is consistent with the smaller end of the stepped thread through hole of the thread screwing sleeve, and the top core is coaxially sleeved in the stepped thread through hole of the thread screwing sleeve and is in threaded connection with the smaller end of the thread screwing sleeve; the positioning shaft shoulder of the top core abuts against the step surface of the stepped threaded through hole of the threaded screwing sleeve; a set distance is reserved between the end surface of the positioning shaft shoulder of the top core and the large end surface of the stepped thread through hole of the thread screwing sleeve; the center of the top core is provided with a through hole, a boss is arranged in the through hole at the end where the shaft shoulder is located, and the other end of the boss extends out of the end where the shaft shoulder of the top core to set the length for butting against the valve core of the elastic self-sealing valve on the airplane so as to open the elastic self-sealing valve on the airplane and enable hydraulic oil to enter the through hole of the top core.)

1. An engine compartment hydraulic oil discharging device, characterized by comprising: a thread screwing sleeve (2) and a top core (4); the center of the thread screwing sleeve (2) is provided with a stepped thread through hole; the top core (4) is a cylindrical structure provided with an external thread, and one end of the top core is provided with a positioning shaft shoulder; the outer diameter of the top core (4) is consistent with the smaller end of the stepped thread through hole of the thread precession sleeve (2), and the top core (4) is coaxially sleeved in the stepped thread through hole of the thread precession sleeve (2) and is in threaded connection with the smaller end of the thread precession sleeve (2); the positioning shaft shoulder of the top core (4) is abutted against the step surface of the stepped threaded through hole of the threaded screwing sleeve (2); a set distance is reserved between the end face of the positioning shaft shoulder of the top core (4) and the large end face of the stepped thread through hole of the thread screwing sleeve (2); the center of the top core (4) is provided with a through hole, a boss is arranged in the through hole at the end where the shaft shoulder is located, and the other end of the boss extends out of the end where the shaft shoulder of the top core (4) is located to set the length of the boss for butting against a valve core of an elastic self-sealing valve on an airplane, so that the elastic self-sealing valve on the airplane is opened, and hydraulic oil enters the through hole of the top core (4).

2. The engine compartment hydraulic oil drain device according to claim 1, wherein the top core (4) is sealed at the joint of a positioning shaft shoulder and a stepped surface of a stepped threaded through hole of the threaded screw-in sleeve (2).

3. The engine room hydraulic oil drain device according to claim 1 or 2, further comprising an anti-drop nut (5), wherein the anti-drop nut (5) is fixed to an outer periphery of the top core (4) protruding from a smaller-diameter end of the stepped threaded through-hole of the threaded driving sleeve (2).

4. The engine compartment hydraulic oil discharging device according to claim 1 or 2, further comprising: the dustproof cap (1), dustproof cap (1) is equipped with the external screw thread, and its one end is equipped with the location shaft shoulder, and recess is seted up at its center, and during dustproof, the great end in aperture of the inside stairstepping screw through-hole of cover (2) is screwed in to dustproof cap (1) screw thread, makes the boss that stretches out in the apical core (4) be located the recess of dustproof cap (1).

5. The engine compartment hydraulic oil discharging device according to claim 1 or 2, further comprising: and one end of the drainage tube (7) is communicated with the top core (4) and is used for draining hydraulic oil in the top core (4).

6. The engine room hydraulic oil drain device according to claim 1 or 2, wherein the boss in the top core (4) is a stepped shaft-like boss.

7. The engine compartment hydraulic oil drain device according to claim 1, wherein an end portion of the boss located in the through hole of the top core (4) is fixed to an inner wall surface of the through hole of the top core (4) by two or more spokes arranged in a radial direction.

8. The engine compartment hydraulic oil discharging device according to claim 3, wherein the anti-drop nut (5) is uniformly provided with more than two stopping impact points in the circumferential direction for fixing the anti-drop nut (5).

9. The engine compartment hydraulic oil drain device according to claim 4, wherein the dust cap (1) is connected to the threaded screw-in sleeve (2) by a connection cord.

10. The engine room hydraulic oil draining device according to claim 4, wherein an annular recession is provided at the joint of the main body part of the dust cap (1) and the positioning shoulder.

Technical Field

The invention relates to the technical field of aviation equipment, in particular to a hydraulic oil discharging device for an engine compartment.

Background

In the process of overhaul of a certain type of airplane, the engine part on the airplane needs to be decomposed, but a large amount of residual oil exists in an engine compartment before the airplane is decomposed, and the residual oil needs to be discharged completely. The oil drain port structure of the aircraft engine compartment is an external thread elastic self-sealing valve, and the elastic valve core is required to be pressed into an oil drain cavity during oil drain so as to enable hydraulic oil to flow out under the action of self weight. In the prior art, the maintenance mode is that an operator holds a screwdriver in a hand, presses a valve core of a self-sealing valve into an oil discharge cavity, and then oil flows into an oil receiving box along the arm of the operator after flowing out. Therefore, the pollution to operators is easy to cause, the operation is inconvenient, and the low working efficiency is easy to cause; therefore, a drainage and discharge device is urgently needed to be designed, which can drain and discharge residual oil in an aircraft engine cabin to an oil receiving box, and meanwhile, the drainage and discharge device is required to be convenient to operate and clean to use.

Disclosure of Invention

In view of this, the invention provides an engine compartment hydraulic oil drainage device, which can conveniently and cleanly drain and discharge hydraulic oil in an aircraft engine compartment to the outside.

The technical scheme of the invention is as follows: an engine compartment hydraulic oil discharging device comprising: a thread screw-in sleeve and a top core; the center of the thread screwing sleeve is provided with a stepped thread through hole; the top core is of a cylindrical structure provided with external threads, and one end of the top core is provided with a positioning shaft shoulder; the outer diameter of the top core is consistent with the smaller end of the stepped thread through hole of the thread precession sleeve, and the top core is coaxially sleeved in the stepped thread through hole of the thread precession sleeve and is in threaded connection with the smaller end of the thread precession sleeve; the positioning shaft shoulder of the top core abuts against the step surface of the stepped threaded through hole of the threaded screwing sleeve; a set distance is reserved between the end face of the top core positioning shaft shoulder and the large end face of the stepped thread through hole of the thread screwing sleeve; the center of the top core is provided with a through hole, a boss is arranged in the through hole at the end where the shaft shoulder is located, and the other end of the boss extends out of the end where the shaft shoulder of the top core to set the length for abutting against a valve core of an elastic self-sealing valve on an airplane so as to open the elastic self-sealing valve on the airplane and enable hydraulic oil to enter the through hole of the top core.

As a preferable scheme, the butt joint of the positioning shaft shoulder of the top core and the step surface of the stepped thread through hole of the thread screwing sleeve is sealed.

As a preferable scheme, the anti-dropping screw further comprises an anti-dropping nut which is fixed on the periphery of the top core extending out of the smaller end of the stepped screw through hole of the screw screwing sleeve.

As a preferable scheme, the method further comprises the following steps: the dustproof cap is provided with external threads, one end of the dustproof cap is provided with a positioning shaft shoulder, the center of the dustproof cap is provided with a groove, and when the dustproof cap is used for dustproof, the dustproof cap is screwed into the end with larger aperture of the stepped thread through hole in the inner part of the threaded sleeve, so that the boss extending out of the top core is positioned in the groove of the dustproof cap.

As a preferable scheme, the method further comprises the following steps: and one end of the drainage tube is communicated with the ejection core and is used for draining hydraulic oil in the ejection core.

Preferably, the boss in the top core is a step shaft-shaped boss.

Preferably, the end of the boss located in the through hole of the top core is fixed on the inner wall surface of the through hole of the top core through more than two spokes arranged along the radial direction.

As a preferable scheme, more than two stop punching points are uniformly arranged on the anti-drop nut in the circumferential direction and used for fixing the anti-drop nut.

Preferably, the dustproof cap is connected with the threaded screw-in sleeve through a connecting rope.

Preferably, an annular tool withdrawal groove is arranged at the joint of the dustproof cap main body part and the positioning shaft shoulder.

Has the advantages that:

(1) the hydraulic oil drainage device is simple in structure, convenient to operate and clean, and can drain and discharge hydraulic oil in the engine compartment of the airplane to the outside.

Drawings

Fig. 1 is a schematic structural diagram of a hydraulic oil discharging device of an aircraft engine compartment according to the invention.

Wherein, 1-dustproof cap, 2-thread screw-in sleeve, 3-sealing rubber ring, 4-top core, 5-anti-drop nut, 6-hose clamp and 7-drainage tube

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.