CN115219213A

CN115219213A - Test method for verifying thermal state cleaning effect of aero-engine

Info

Publication number: CN115219213A
Application number: CN202210982840.7A
Authority: CN
Inventors: 金洪江; 蔡百鸣; 宋鹏磊; 胡忠仲; 朱夏雯; 陆慧华
Original assignee: China Hangfa Changzhou Lanxiang Machinery Co ltd
Current assignee: China Hangfa Changzhou Lanxiang Machinery Co ltd
Priority date: 2020-07-09
Filing date: 2020-07-09
Publication date: 2022-10-21
Also published as: CN111829788B; CN111829788A

Abstract

The invention relates to a test method for verifying the thermal state cleaning effect of an aircraft engine, which comprises the steps of coating gouache on an axial flow compressor rotor combination and an axial flow compressor rectifier of the aircraft engine, carrying out thermal state washing on the engine, and evaluating the cleaning effect by observing the residual condition of the washed gouache; the selected gouache is yellow or red gouache, has bright color, has larger color contrast with the rotor combination of the axial flow compressor of the aircraft engine and the rectifier of the axial flow compressor, and is easy to observe; when the cleaning is carried out, the aircraft engine is in a starting state, the cleaning in a hot vehicle state is realized, and the cleaning effect is improved.

Description

Test method for verifying thermal state cleaning effect of aero-engine

Technical Field

The invention relates to the technical field of aero-engine parts, in particular to a test method for verifying the thermal cleaning effect of an aero-engine.

Background

The air inlet channel of the engine needs to be cleaned after the last flight every day is finished, salt particles are removed, the waiting time of a conventional cold cleaning mode is long, and great inconvenience is brought to the use and maintenance of a user. The aircraft engine is designed with a cleaning system from the consideration of maintainability, and hot washing is realized, so that the engine cleaning time is shortened, and the maintenance efficiency is improved. In the hot washing process of the engine, parameters such as washing flow, washing pressure, nozzle atomization granularity, atomization angle and nozzle injection angle can directly influence the flowing and distribution conditions of the washing liquid in the air inlet channel, so that the whole washing effect is directly influenced. In order to effectively improve the cleaning effect of the engine, appropriate cleaning parameters need to be determined, and how to verify the thermal cleaning effect of the aircraft engine is a technical problem which needs to be solved urgently by a technical person in the field.

Disclosure of Invention

The invention aims to provide a test method for verifying the thermal cleaning effect of an aircraft engine, which is simple to operate and easy to judge.

In order to solve the technical problems, the invention discloses a method for evaluating the cleaning effect by coating gouache on an axial flow compressor rotor assembly and an axial flow compressor rectifier of an aircraft engine, carrying out hot-state washing on the engine and observing the residual condition of the gouache after washing.

Specifically, the test method for verifying the thermal state cleaning effect of the aircraft engine provided by the invention comprises the following steps:

A. coating gouache on an aircraft engine axial flow compressor rotor combination and an axial flow compressor rectifier;

B. assembling an aircraft engine, testing the aircraft engine on a stand, starting the aircraft engine, stabilizing the ground slow turning state for 5-10min, opening a cleaning vehicle, and introducing cleaning liquid to carry out thermal cleaning on the engine;

C. after the cleaning is finished, the aeroengine ground slow vehicle continues to work for 30-60 seconds to dry the aeroengine, and the aeroengine stops;

D. and decomposing the lower stand of the aircraft engine, observing the residual conditions of the axial flow compressor rotor combination and the gouache on the axial flow compressor rectifier, and judging the cleaning effect.

Further, in the step B, the cleaning solution is normal-temperature tap water, the cleaning flow is 0.6L/min-0.8L/min, and the total cleaning amount is 7L-8L.

Further, in the step A, the selected gouache is yellow or red gouache which is bright in color and easy to observe.

The invention has the technical effects that: (1) Compared with the prior art, the test method for verifying the thermal-state cleaning effect of the aircraft engine has the advantages that the cleaning effect can be visually evaluated by observing the residual condition of the washed gouache after the thermal-state washing of the aircraft engine is carried out by coating the gouache on the axial flow compressor rotor combination and the axial flow compressor rectifier of the aircraft engine and carrying out the thermal-state washing on the aircraft engine; (2) The selected gouache is yellow or red, has bright color, has larger color contrast with the rotor combination of the axial flow compressor of the aircraft engine and the rectifier of the axial flow compressor, and is easy to observe; (3) When the cleaning is carried out, the aircraft engine is in a starting state, the cleaning in a hot vehicle state is realized, and the cleaning effect is improved.

Drawings

The invention is described in further detail below with reference to the drawings of the specification:

FIG. 1 is a photograph of an axial compressor rotor assembly of an aircraft engine after application of a gouache prior to combined hot cleaning;

FIG. 2 is a photograph of an axial flow compressor rectifier of an aircraft engine after application of a gouache prior to thermal cleaning;

FIG. 3 is a photograph of an axial compressor rotor assembly of an aircraft engine after thermal cleaning;

FIG. 4 is a photograph of an aircraft engine after thermal cleaning of an axial compressor rectifier.

Detailed Description

Example 1

The test method for verifying the thermal cleaning effect of the aircraft engine comprises the following steps:

A. coating yellow gouache pigment on an axial flow compressor rotor assembly and an axial flow compressor rectifier of an aircraft engine;

B. assembling an aircraft engine, testing the aircraft engine on a rack, starting the aircraft engine, stabilizing the ground slow turning state for 5min, opening a cleaning vehicle, and introducing cleaning liquid to carry out thermal cleaning on the aircraft engine; the cleaning solution is normal-temperature tap water, the cleaning flow is 0.6L/min, and the total cleaning amount is 7L;

C. after the cleaning is finished, the aeroengine ground slow vehicle continues to work for 30 seconds to dry the aeroengine, and the aeroengine stops;

FIG. 1 is a photograph of an axial compressor rotor assembly coated with a gouache prior to thermal cleaning; FIG. 2 is a photograph of an axial compressor rectifier after application of a gouache prior to thermal cleaning; the effect of the axial flow compressor rotor combination after thermal cleaning is shown in fig. 3, and the effect of the axial flow compressor rectifier after thermal cleaning is shown in fig. 4, and as can be seen from fig. 3 and 4, the effect of the axial flow compressor rotor combination and the axial flow compressor rectifier after thermal cleaning can be clearly and intuitively determined.

Example 2

A. coating red gouache on an aircraft engine axial flow compressor rotor combination and an axial flow compressor rectifier;

B. assembling an aircraft engine, testing the aircraft engine on a rack, starting the aircraft engine, stabilizing the ground slow turning state for 7min, opening a cleaning vehicle, and introducing cleaning liquid to carry out thermal cleaning on the aircraft engine; the cleaning solution is normal-temperature tap water, the cleaning flow is 0.7L/min, and the total cleaning amount is 7L;

C. after the cleaning is finished, the aeroengine ground slow vehicle continues to work for 60 seconds to dry the aeroengine, and the aeroengine stops;

Example 3

B. assembling an aircraft engine, testing the aircraft engine on a rack, starting the aircraft engine, stabilizing the ground slow turning state for 10min, opening a cleaning vehicle, and introducing cleaning liquid to carry out thermal cleaning on the aircraft engine; the cleaning solution is normal-temperature tap water, the cleaning flow is 0.8L/min, and the total cleaning amount is 7L;

C. after the cleaning is finished, the aeroengine ground slow vehicle continues to work for 45 seconds to dry the aeroengine, and the aeroengine stops;

It should be understood that the above examples are only for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And such obvious changes and modifications as fall within the spirit of the invention are deemed to be within the scope of the invention.

Claims

1. A test method for verifying the thermal cleaning effect of an aircraft engine is characterized by comprising the following steps:

A. coating gouache on an aircraft engine axial flow compressor rotor assembly and an axial flow compressor rectifier, wherein the selected gouache is yellow or red;