CN215525065U

CN215525065U - Aircraft engine cold running equipment

Info

Publication number: CN215525065U
Application number: CN202121932311.3U
Authority: CN
Inventors: 王冠华
Original assignee: Zhejiang Huaqing Aviation Engine Technology Co ltd
Current assignee: Zhejiang Huaqing Aviation Engine Technology Co ltd
Priority date: 2021-08-17
Filing date: 2021-08-17
Publication date: 2022-01-14
Anticipated expiration: 2031-08-17

Abstract

The utility model relates to an aircraft engine cold running device, wherein a workbench of a frame is provided with a mounting groove for accommodating an aircraft engine, a driving device is arranged at one side of the mounting groove, an output shaft of the driving device extends towards the direction of the mounting groove, the driving device replaces the ignition of the aircraft engine to directly drive the aircraft engine to rotate, an oil delivery pipe in an oil supply assembly is used for delivering oil to the aircraft engine, the environment of the aircraft engine during working is simulated, and the data of a test experiment can be ensured to be more accurate; meanwhile, the oil flowing out of the aero-engine is blocked by the baffle plate, so that the blocked oil enters the oil storage bin below the baffle plate under the action of gravity, and the same batch of oil can circulate on a flow path formed among the oil storage bin, the oil delivery pipe and the baffle plate in a reciprocating mode under the action of negative pressure generated by rotation of the aero-engine, and the oil storage bin is used repeatedly and very conveniently.

Description

Aircraft engine cold running equipment

Technical Field

The utility model relates to the field of aero-engine experiments, in particular to aero-engine cold running equipment.

Background

The aircraft engine is one of the most important parts of the aircraft and is a power source for the flight of the aircraft. The operating mode of aeroengine is often very abominable, and whether can guarantee under extreme circumstances that the output of power is very crucial, consequently when researching and developing, need carry out a large amount of simulation experiments to aeroengine to ensure its stability of using.

Generally, the test of an aircraft engine is generally carried out under ignition conditions, with various parameters of the instrument being recorded and the data being analyzed and integrated later. The rotor and the stator of a brand-new engine do not well break-in, the rotor and the stator generally need to wait for gradual break-in from a low rotating speed to a high rotating speed, a coating on the stator is worn off, the rotating speed of the engine in an ignition state is kept above 15000rpm, and if the engine ignition is directly adopted for rotating speed simulation, the rotor and the stator do not pass through a low-speed break-in process, and engine blades can be damaged. In an ignition state, the rotating speed of the engine cannot be accurately controlled, and +/-2% fluctuation exists, so that inaccuracy of test data can be caused.

The Chinese invention with the application number of CN202010645080.1 discloses a comprehensive test device and a test method for the dynamic seal leakage, heat transfer, friction and abrasion characteristics of an aero-engine, wherein the test device simulates different working conditions of the engine during use, different performances such as sealing, heat transfer and friction are tested by utilizing a servo motor, a torque and speed sensor, a test cavity and an electric slip ring which are sequentially connected, the test cavity is divided into a bearing cavity section and a sealing element test section, and a main shaft penetrates through the middle part of the test cavity; the servo motor and the torque rotating speed sensor are supported by a motor support, and the test cavity is supported by a test cavity fixing support and a test cavity adjustable support together.

Although the servo motor is adopted to replace ignition to realize power simulation in the experimental device, the working condition of the aero-engine is reproduced, the aero-engine usually has fuel oil participation when in use, and although the device also relates to an oil way, the oil is used for lubrication, so that the use scene of the aero-engine cannot be completely restored, and further improvement is needed.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem of providing the aircraft engine cold running equipment capable of effectively reducing the working environment of the aircraft engine aiming at the current situation of the prior art.

The technical scheme adopted by the utility model for solving the technical problems is as follows: an aircraft engine cold-running apparatus comprising:

the aircraft engine mounting device comprises a frame, a mounting plate and a mounting plate, wherein the frame is provided with a workbench which is provided with a mounting groove for accommodating an aircraft engine;

the driving device is used for driving the aircraft engine to rotate, is arranged on one side of the mounting groove, and extends the output shaft of the driving device towards the direction of the mounting groove;

still including the fuel feeding unit, the fuel feeding unit is including being used for to the defeated oil pipe of aeroengine fuel feeding, can carry out the baffle that keeps off the flow to aeroengine exhaust oil and be used for holding the oil storage storehouse of the oil that baffle department flowed down, defeated oil pipe's entrance point with the exit end fluid intercommunication in oil storage storehouse, the oil storage storehouse is arranged the below of baffle.

Specifically, the table top of the workbench is at least partially recessed downwards to form the mounting groove, an oil return hole is further formed in the bottom wall of the mounting groove at a position corresponding to the baffle, and the oil return hole is communicated with the oil storage bin in a fluid mode.

In order to facilitate the oil to flow into the oil storage bin, the bottom wall of the mounting groove is preferably arranged to be inclined downwards from one side adjacent to the driving device to the oil return hole.

In order to ensure that defeated oil pipe can carry the oil to aeroengine, specifically, defeated oil pipe wears to establish on the workstation, and its oil outlet end has the connector of horizontal arrangement.

In order to adjust the position of the aero-engine conveniently, the aero-engine cold operation equipment further comprises two sets of sliding rail assemblies, and the sliding rail assemblies are arranged on the upper edges of the two side walls of the mounting groove respectively.

Specifically, the slide rail assembly comprises a slide way and a slide block in sliding fit with the slide way, the slide way extends along the length direction of the installation groove, and a positioning column used for positioning the aircraft engine is arranged on the slide block in an upward protruding mode.

Preferably, the output end of the driving device is provided with a coupling used for being connected with an aircraft engine.

In order to ensure that the oil sprayed on the baffle plate does not splash, the upper end surface of the baffle plate is preferably an arc surface protruding upwards.

The driving means may take various forms, and preferably, the driving means employs a motor as a power source.

Compared with the prior art, the utility model has the advantages that: in the aircraft engine cold running equipment, the driving device replaces ignition of the aircraft engine to directly drive the aircraft engine to rotate, and an oil delivery pipe in the oil supply assembly is used for delivering oil to the aircraft engine, so that the environment of the aircraft engine during working is simulated, and more accurate data of a test experiment can be ensured; meanwhile, the oil flowing out of the aero-engine is blocked by the baffle plate, so that the blocked oil enters the oil storage bin below the baffle plate under the action of gravity, and the same batch of oil can circulate on a flow path formed among the oil storage bin, the oil delivery pipe and the baffle plate in a reciprocating mode under the action of negative pressure generated by rotation of the aero-engine, and the oil storage bin is used repeatedly and very conveniently.

Drawings

FIG. 1 is a schematic overall structure diagram of an aircraft engine cold-running device in an embodiment of the utility model;

FIG. 2 is a schematic view of FIG. 1 from another angle after the aircraft engine is omitted.

Detailed Description

The utility model is described in further detail below with reference to the accompanying examples.

As shown in fig. 1 to 2, the aircraft engine cold-running device according to a preferred embodiment of the present invention includes a frame 1, a driving apparatus 2, and an oil supply unit. The frame 1 has a workbench 10, the workbench 10 has a mounting groove 1a for accommodating an aircraft engine, the mounting groove 1a may have different design forms, in this embodiment, the table surface of the workbench 10 is at least partially recessed to form the mounting groove 1 a. The above-mentioned driving device 2 is used for driving the rotation of the aircraft engine, the driving device 2 is arranged on one side of the mounting groove 1a, and the output shaft of the driving device 2 extends towards the direction of the mounting groove 1a, the driving device 2 in the embodiment adopts a motor as a power source, and the output end of the driving device 2 (i.e. the motor) is provided with a coupling 5 for connecting with the aircraft engine.

In order to ensure that the oil supply assembly can form an oil circuit circulation, the oil supply assembly comprises an oil delivery pipe 31, a baffle 32 and an oil storage bin 33, wherein the oil delivery pipe 31 is used for supplying oil to the aircraft engine, the oil delivery pipe 31 is arranged on the workbench 10 in a penetrating way, and the oil outlet end of the oil delivery pipe is provided with a connecting head 311 which is horizontally arranged. The baffle 32 is used for blocking the flow of oil discharged by the aircraft engine, the baffle 32 can be arranged at the oil outlet end of the aircraft engine in actual use, and the upper end surface of the baffle 32 is an arc-shaped surface protruding upwards to avoid splashing of the oil.

The oil storage bin 33 is used for storing oil flowing down from the baffle 32, specifically, the inlet end of the oil pipeline 31 in this embodiment is in fluid communication with the outlet end of the oil storage bin 33, and the oil storage bin 33 is disposed below the baffle 32. In order to ensure that the oil blocked by the baffle 32 can flow back to the oil storage bin 33, an oil return hole 30 is further formed in the bottom wall of the mounting groove 1a at a position corresponding to the baffle 32, and the oil return hole 30 is in fluid communication with the oil storage bin 33. The mounting groove 1a may be of various forms, and in the present embodiment, the mounting groove 1a is arranged with a bottom wall inclined downward from a side adjacent to the driving unit 2 toward the oil return hole 30. Thus, even if the oil overflows into the mounting groove 1a, the oil returns to the oil storage bin 33 from the oil return hole 30 under the action of gravity.

Certainly, in order to facilitate the position adjustment of the aircraft engine, the aircraft engine cold running device further comprises two sets of sliding rail assemblies 4, and the two sets of sliding rail assemblies 4 are respectively arranged on the upper edges of the two side walls of the installation groove 1 a. The slide rail assembly 4 includes a slide rail 41 and a slide block 42 slidably engaged with the slide rail 41, the slide rail 41 extends along the length direction of the mounting groove 1a, and the slide block 42 is provided with a positioning column 421 protruding upwards for positioning the aircraft engine.

The term "fluid communication" as used herein refers to a spatial relationship between two components or portions (hereinafter collectively referred to as a first portion and a second portion, respectively), i.e., a fluid (gas, liquid or a mixture of both) can flow along a flow path from the first portion and/or be transported to the second portion, and may be a direct communication between the first portion and the second portion, or an indirect communication between the first portion and the second portion via at least one third element, such as a fluid channel, e.g., a pipe, a channel, a duct, a flow guide, a hole, a groove, or a chamber that allows a fluid to flow through, or a combination thereof.

Also, directional terms, such as "front," "rear," "upper," "lower," "left," "right," "side," "top," "bottom," and the like, may be used in the description and claims to describe various example structural portions and elements of the utility model, but are used herein for convenience of description only and are determined based on the example orientations shown in the figures. Because the disclosed embodiments of the present invention may be oriented in different directions, the directional terms are used for descriptive purposes and are not to be construed as limiting, e.g., "upper" and "lower" are not necessarily limited to directions opposite to or coincident with the direction of gravity.

Claims

1. An aircraft engine cold-running apparatus comprising:

the aircraft engine mounting frame comprises a frame (1) and a workbench (10), wherein the workbench (10) is provided with a mounting groove (1a) for accommodating an aircraft engine;

the driving device (2) is used for driving the aircraft engine to rotate, the driving device (2) is arranged on one side of the mounting groove (1a), and an output shaft of the driving device extends towards the direction of the mounting groove (1 a);

the aircraft fuel supply device is characterized by further comprising a fuel supply assembly, wherein the fuel supply assembly comprises a fuel supply oil delivery pipe (31) for supplying fuel to the aircraft engine, a baffle plate (32) capable of blocking the flow of the fuel discharged by the aircraft engine and a fuel storage bin (33) for containing the fuel flowing down from the baffle plate (32), the inlet end of the fuel delivery pipe (31) is communicated with the outlet end of the fuel storage bin (33) in a fluid mode, and the fuel storage bin (33) is arranged below the baffle plate (32).

2. An aircraft engine cold-running apparatus according to claim 1, wherein: the table top of the workbench (10) is at least partially sunken downwards to form the mounting groove (1a), an oil return hole (30) is further formed in the bottom wall of the mounting groove (1a) at a position corresponding to the baffle (32), and the oil return hole (30) is communicated with an oil storage bin (33) in a fluid mode.

3. An aircraft engine cold-running apparatus according to claim 2, wherein: the bottom wall of the mounting groove (1a) is arranged from one side adjacent to the driving device (2) to incline downwards towards the oil return hole (30).

4. An aircraft engine cold-running apparatus according to claim 3, wherein: defeated oil pipe (31) wear to establish on workstation (10), and its oil outlet end has connector (311) of horizontal arrangement.

5. An aircraft engine cold-running apparatus according to claim 4, wherein: the sliding rail component (4) is further included, and the sliding rail component (4) is provided with two groups of sliding rail components which are respectively arranged on the upper edges of the two side walls of the mounting groove (1 a).

6. An aircraft engine cold-running apparatus according to claim 5, wherein: slide rail set spare (4) include slide (41) and with slide (41) sliding fit's slider (42), slide (41) extend along the length direction of mounting groove (1a), slider (42) upwards protruding be equipped with be used for fixing a position aeroengine's reference column (421).

7. An aircraft engine cold-running apparatus according to claim 6, wherein: and the output end of the driving device (2) is provided with a coupling (5) used for being connected with an aircraft engine.

8. An aircraft engine cold-running apparatus according to claim 7, wherein: the upper end surface of the baffle (32) is an arc surface protruding upwards.

9. An aircraft engine cold-running apparatus according to any one of claims 1 to 8, wherein: the driving device (2) adopts a motor as a power source.