CN114017158A

CN114017158A - Method for reducing oil supply fluctuation of aviation lubricating oil pump and aviation lubricating oil pump

Info

Publication number: CN114017158A
Application number: CN202111405355.5A
Authority: CN
Inventors: 侯宏建; 左斌辉; 苏壮; 谷智赢; 胡兴龙
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2021-11-24
Filing date: 2021-11-24
Publication date: 2022-02-08

Abstract

The utility model relates to a lubricating oil pump field, for a method for reducing aviation lubricating oil pump fuel feeding is undulant, through confirming the number of teeth of single-stage rotor earlier, confirm first angle, then divide into first angle averagely a plurality of to obtain the second angle, divide into a plurality of rotors with single-stage rotor averagely, the thickness of every rotor is the fraction of former rotor, the second angle of deviation between arbitrary adjacent rotor, set up the circular baffle who seals two rotors between two adjacent rotors, have the phase difference between arbitrary adjacent rotor when lubricating oil pump during operation like this, when the outlet pressure of a rotor is great, another can be less, both compensate each other so that the outlet pressure fluctuation of lubricating oil pump can be in less within range, thereby reduce the injury to engine sliding system effectively, improve the life-span and the reliability of the corresponding spare part of engine.

Description

Method for reducing oil supply fluctuation of aviation lubricating oil pump and aviation lubricating oil pump

Technical Field

The application belongs to the field of lubricating oil pumps, and particularly relates to a method for reducing oil supply fluctuation of an aviation lubricating oil pump and the aviation lubricating oil pump.

Background

According to a large number of complete machine test runs of a certain type of engine, the pressure of the outlet of an engine lubricating oil supply pump is fluctuated, is not constant and is larger. The existence of the wave can bring adverse effect to the engine, the higher the amplitude of the wave is, the greater the damage to an engine lubricating oil system is, and the greater the potential safety hazard to the safety of the engine is.

If the existing lubricating oil pump adopts a single-stage rotor, the fluctuation level of the oil supply pressure of the lubricating oil pump is large, so that potential safety hazards are brought to a lubricating oil system of an engine; the single-stage rotor which is too thick can affect the oil absorption filling property, the influence is larger when the pressure of an oil absorption inlet is lower, and the efficiency of the pump is lower; the large pressure fluctuation of the oil supply of the lubricating oil pump can cause the vibration of the lubricating oil pump and related pipelines, and reduce the service life of the lubricating oil pump and the related pipelines.

Therefore, how to reduce the fluctuation of the oil supply pressure of the lubricating oil pump and improve the stability of the operation of the lubricating oil pump is a problem to be solved.

Disclosure of Invention

The application aims to provide a method for reducing oil supply fluctuation of an aviation lubricating oil pump and the aviation lubricating oil pump, so as to solve the problem that the pressure fluctuation of an outlet of the lubricating oil pump influences the efficiency of the lubricating oil pump in the prior art.

The technical scheme of the application is as follows: a method for reducing oil supply fluctuation of an aviation lubricating oil pump comprises the steps of determining the number of teeth of a single-stage rotor, and obtaining a first angle between two adjacent teeth according to the number of teeth; averagely dividing the first angle into a plurality of angles, thereby obtaining a second angle; the single-stage rotor is split into a plurality of rotors to coaxially rotate, a second angle is deflected between two adjacent rotors, a circular partition plate for closing the two rotors is arranged between the two adjacent rotors, and the thickness of each rotor is the number of stages of the rotor divided by the thickness of the original single-stage rotor.

Preferably, the number of the rotors is 4, the second angle is 45 °, and the number of the rotors on the same side is 2.

Preferably, the thickness of the circular partition is the same as that of the rotor.

As a specific implementation mode, the lubricating oil pump for the aircraft engine comprises a shell, wherein an inner cavity is formed in the shell; the inner rotor and the outer rotor are arranged in the inner cavity of the shell, the inner rotor and the outer rotor are in multiple stages, any inner rotor is meshed with the outer rotor in the same stage, a second angle is deflected between any two adjacent inner rotors or outer rotors, the second angle is the angle between any two adjacent teeth of any rotor divided by the number of stages of the rotors, a circular partition plate for sealing the adjacent rotors is arranged between any two adjacent rotors, and the thickness of the original single-stage rotor divided by the number of stages of the rotors is the thickness of each rotor.

The utility model provides a method for reducing aviation lubricating oil pump fuel feeding is undulant, through the number of teeth of confirming single-stage rotor earlier, confirm first angle, then divide into a plurality ofly with first angle averagely and obtain the second angle, divide into a plurality of rotors with single-stage rotor averagely, the thickness of every rotor is the fraction of former rotor, deviation second angle between arbitrary adjacent rotor, set up the circular baffle of two rotors of seal between two adjacent rotors, have the phase difference between arbitrary adjacent rotor when lubricating oil pump work like this, when the export pressure of a rotor is great, another can be less, both compensate each other so that the export pressure fluctuation of lubricating oil pump can be in less within range, thereby reduce the injury to engine sliding system effectively, improve the life-span and the reliability of the corresponding spare part of engine.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a schematic overall flow diagram of the present application;

FIG. 2 is a schematic structural view of a dual stage rotor of the present application;

FIG. 3 is a schematic structural view of a three-stage rotor according to the present application;

FIG. 4 is a graph illustrating pressure fluctuations for a twin rotor of the present application;

FIG. 5 is a partial block diagram of a single-stage rotor lubricating oil pump of the present application;

FIG. 6 is a partial block diagram of a lube pump under the dual stage rotor of the present application.

1. An outer rotor; 2. an inner rotor; 3. a housing.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

A method for reducing oil supply fluctuation of an aviation lubricating oil pump is shown in figures 1-3, and the working process of a traditional pan-cycloid inner 4-tooth rotor gear pump is analyzed, so that oil suction-oil discharge actions are repeated for 4 times in each rotation, the oil discharge amount of an outlet is limited by the structure of a rotor, the oil discharge amount is not constant at each moment, namely, the outlet pressure is not constant, the waveform of the wave is regular and similar to a sine wave, the frequency is the same as the number of 2 inner rotors, and the difference value between the wave crest and the wave trough is the fluctuation amount of the lubricating oil pressure of the pump. In order to reduce the difference value between the wave crest and the wave trough, the structure of the inner rotor 2 of the single-stage oil supply pump is changed into a structure of a multi-stage inner rotor 2 with phase difference, so that the pressure fluctuation is reduced. To obtain a second angle

The method comprises the following specific steps:

step S100, determining the number of teeth of the single-stage rotor, and obtaining a first angle between two adjacent teeth according to the number of teeth;

step S200, averagely dividing the first angle into a plurality of angles so as to obtain a second angle;

and step S300, splitting the single-stage rotor into a plurality of rotors to coaxially rotate, deflecting the adjacent two rotors by a second angle, arranging a circular partition plate for sealing the two rotors between the two adjacent rotors, and dividing the thickness of each rotor by the number of the rotors.

Through setting the multi-stage rotors to coaxially rotate, and the different rotors have uniformly set phase differences, when the outlet pressure of one rotor is higher, the other rotors are in the positions with lower outlet pressure in the same state; when the outlet pressure of one rotor is lower, the other rotors are in the positions with higher outlet pressure in the same state; therefore, at the outlet of the lubricating oil pump, the pressure fluctuation formed by combining different rotors is in a larger state, so that the damage to the sliding system of the engine is effectively reduced, and the service life and the reliability of corresponding parts of the engine are improved.

Meanwhile, the thickness of each rotor in the multistage rotors is reduced, the time required by the oil absorption of the rotors is short, and the filling performance is better, so that the high-altitude performance of the pump can be greatly improved.

The circular baffle is located the axial below of single-stage rotor among the existing lubricating oil pump, now through separating into the polylith with circular baffle and locate between arbitrary adjacent rotor, circular baffle like this can also prevent to take place the flow of lubricating oil between arbitrary adjacent rotor when having the function of itself.

Preferably, the number of the rotor teeth is 4, the first angle is 90 °, the second angle is 45 °, the number of the rotors on the same side is 2, in the working process, every 1 rotation, the "oil absorption-oil discharge" action is changed from 4 times to 8 times, the outlet pressure is formed by superposing and combining pressure waves (approximate sine waves) generated by the two-stage rotors, in order to minimize the fluctuation amount, the phase difference of the two waves should be 1/2 cycles, that is, the assembly angle of the inner rotor 2 is 45 ° different. And by analogy, the phase difference of the three-stage rotors is 1/3 cycles, namely the assembly angles of the inner rotors 2 are different by 30 degrees, and the phase difference of the n-stage rotors is 1/n cycle.

As shown in fig. 4, the upper and lower lines are pressure fluctuation conditions with different phases, and the middle line is pressure fluctuation condition after combination, it can be seen that the pressure fluctuation amount of the lubricating oil is obviously reduced after the two-stage rotor with phase difference is adopted.

Preferably, the thickness of the circular partition is the same as or similar to that of the rotor, and the circular partition can stably support the rotor and effectively close the cavity formed between the adjacent rotor and the housing 3, so that each rotor can stably work.

As a specific embodiment, an aircraft engine lubricating oil pump, as shown in fig. 5 and 6, includes a housing 3, wherein an inner cavity is provided in the housing 3; the inner rotor 2 and the outer rotor 1 are arranged in an inner cavity of the shell 3, the inner rotor 2 and the outer rotor 1 are both in multiple stages, any inner rotor 2 is meshed with the outer rotor 1 in the same stage, any adjacent inner rotor 2 or outer rotor 1 deflects by a second angle, the second angle is the angle between any two adjacent teeth of any rotor divided by the number of stages of the rotors, a circular partition plate (not shown in the figure and at the position of a gap between two adjacent rotors) for sealing the adjacent rotors is arranged between any two adjacent rotors, and the thickness of the original single-stage rotor is divided by the number of stages of the rotors to be the thickness of each rotor.

The single-stage rotor is divided into multiple stages, and any one of the inner rotor 2 and the outer rotor 1 which are correspondingly arranged are guaranteed to be meshed with each other, so that when the lubricating oil pump works, because the rotors which are coaxially arranged have uniformly arranged phase differences, the pressure of the rotors in different stages of the lubricating oil pump is mutually supplemented when the lubricating oil pump works, and the pressure fluctuation at the outlet of the lubricating oil pump is guaranteed to be in a smaller state, thereby effectively reducing the damage to an engine sliding system and improving the service life and the reliability of corresponding parts of an engine.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A method for reducing oil supply fluctuation of an aviation lubricating oil pump is characterized by comprising the following steps: comprises the steps of (a) preparing a mixture of a plurality of raw materials,

determining the number of teeth of the single-stage rotor, and obtaining a first angle between two adjacent teeth according to the number of teeth;

averagely dividing the first angle into a plurality of angles, thereby obtaining a second angle;

the single-stage rotor is split into a plurality of rotors to coaxially rotate, a second angle is deflected between two adjacent rotors, a circular partition plate for closing the two rotors is arranged between the two adjacent rotors, and the thickness of each rotor is the number of stages of the rotor divided by the thickness of the original single-stage rotor.

2. The method for reducing fluctuations in the oil supply to an aviation fuel pump of claim, wherein: the number of teeth of the rotor is 4, the second angle is 45 degrees, and the number of the rotors on the same side is 2.

3. The method for reducing fluctuations in the oil supply to an aviation fuel pump of claim, wherein: the thickness of the circular partition is the same as that of the rotor.

4. An aeroengine lubricating oil pump which characterized in that: comprises a shell (3), wherein an inner cavity is arranged in the shell (3); locate inner rotor (2) and outer rotor (1) of casing (3) inner chamber, inner rotor (2) and outer rotor (1) all have the multistage, arbitrary inner rotor (2) and the outer rotor (1) intermeshing at the same level, the second angle that deflects between arbitrary adjacent inner rotor (2) or outer rotor (1), the second angle is the degree of the angle between the adjacent two teeth of arbitrary rotor divided by the rotor, is equipped with the circular baffle closed with adjacent rotor between arbitrary two adjacent rotors, and the thickness of former single-stage rotor is the thickness of every rotor divided by the degree of rotor.