CN203051237U - Surge-preventing structure for aero-engine compressor - Google Patents

Abstract

The utility model relates to an aero-engine compressor anti-breathing structure, in which a stator ring is installed inside a compressor case, on which are arranged circumferentially uniform stator blades, the compressor rotor is located in the compressor case 1 and is equipped with rotor blades, At the position of the stator vane on the stator ring, there is a radial vent hole in the middle of every two stator vanes, and a vent hole with a diameter larger than the radial vent hole is opened at the corresponding position on the compressor casing and the intermediate casing. The utility model eliminates the possibility of stall and surge caused by too large angle of attack; the flow condition is also improved, so that surge can be effectively prevented. The advantage of this structure is that it can improve the characteristics of the compressor, expand the stable working range, and can be used to prevent the "surge before and after the vortex" type surge. At the same time, it has the advantages of convenient processing, low dimensional accuracy, simple structure, low cost, and reduced gas characteristics of loss.

Description

Aeroengine compressor anti-surge structure

technical field

The utility model relates to an anti-breathing structure of an aero-engine compressor.

Background technique

When the multi-stage axial flow compressor of an aero-engine works under variable working conditions, when the inlet flow decreases, the angle of attack is positive, and the air flow will be separated on the back side of the blade. In this area, once the separation occurs, there will be continuous The trend of development continues, therefore, the excessive positive attack angle can make the operation of the compressor unstable, thus causing surge. When the engine speed is lower than the design speed, the first few stages of compressors will surge due to the excessive angle of attack, while the angle of attack in the last stage will decrease, and the pressure rise and efficiency will decrease rapidly. When the operating conditions deviate greatly from the designed operating conditions , the pressure rise value of the final stage is likely to become a negative value, and it is in the state of the turbine. In the above situation, we become the state of "swirling and vortex", which is a phenomenon that is easy to occur when the multi-stage axial flow compressor deviates from the design condition.

There are anti-surge measures on the compressors of modern high boost ratio aero-engines. The anti-surge devices can be divided into the following types according to the mechanism: deflation mechanism, setting of rotatable inlet guide vanes and rotatable stator blades, and design of variable camber Imported guide vanes, design of intake air treatment casing structure and multi-rotor engine structure, etc., the principle of the air release mechanism is to release air from the middle or final stage of the compressor. This method is simple and effective, but the disadvantage is that the supercharged If the air is released in vain, the efficiency of the compressor will be reduced; the installation of the rotatable inlet guide vane and the rotatable stator vane is to rotate the inlet guide vane by an angle when the compressor is working in a non-design state, so that the compressor inlet is pre-set. The screw quantity changes accordingly, so that the intake angle of attack of the first-stage working blade can be restored to the state close to the design state, the separation of the air flow on the back of the blade is eliminated, and the occurrence of surge phenomenon is avoided; the inlet with variable camber is designed Guide vane, the vane is composed of front and rear sections, the front section is fixed to adapt to the incoming flow, and the rear section can be continuously adjusted to ensure the air intake angle of attack required by the working blade; the design of the intake treatment casing structure refers to the Narrow slits, slots, holes, etc. are opened on the wall of the air intake casing of the engine, which can delay the stall of the blades and expand the surge margin of the compressor; the dual-rotor engine has more work than the single-rotor engine under the same boost ratio. The range is wide, the number of supercharging is less than that of the lower stages, and the non-design state has the advantages of high efficiency. The structure, support, force transmission and lubrication of the three rotors are all complicated, and the cost is high.

Contents of the invention

The purpose of the utility model is to provide a simple and efficient anti-surge structure of an aero-engine compressor, which can improve the characteristics of the compressor, expand the stable working range, and can be used to prevent "surge in the front and vortex in the back".

The technical scheme of the utility model is: the anti-breathing structure of the aero-engine compressor includes a compressor casing, an intermediary casing and a stator ring, the intermediary casing is installed on the compressor casing, and the stator ring is installed inside the compressor casing, and the stator ring is There are stator blades evenly distributed in the circumferential direction, the compressor rotor 4 is located in the compressor casing and installed with rotor blades, the rotor blades and the stator blades are interlaced to form an inner channel, and the outer part of the intermediate casing is an outer channel, which is located on the stator ring. For the position of the stator vane, there is a radial vent hole in the middle of every two stator vanes, and a vent hole with a diameter larger than the radial vent hole is opened at the corresponding position on the compressor casing and the intermediate casing. There are 76 vent holes, the diameter of the vent holes on the stator ring is 5mm, and the diameter of the vent holes on the compressor casing and the intermediate casing is 6mm.

When the utility model is in use, the gas in the inner channel of the compressor enters the annular cavity between the outer ring of the stator ring and the compressor casing through the vent hole of the stator ring, and then passes through the release of the compressor casing and the intermediate casing. The stomata flow into the outer duct. Through deflation, the flow rate of the first-stage compressor increases, and the corresponding axial velocity and flow coefficient increase, thereby eliminating the possibility of stall and surge caused by excessive attack angle; due to the improvement of the working conditions of the first-stage compressor and the pressure The ratio and efficiency are improved, the air density of the final stage is increased, and the flow conditions are also improved, so that surge can be effectively prevented. The advantage of this structure is that it can improve the characteristics of the compressor, expand the stable working range, and can be used to prevent the "surge before and after the vortex" type surge. At the same time, it has the advantages of convenient processing, low dimensional accuracy, simple structure, low cost, and reduced gas characteristics of loss.

Description of drawings

Fig. 1 is the structural representation of the utility model.

Detailed ways

As shown in the figure, the anti-puff structure of an aero-engine compressor includes a compressor casing 1, an intermediate casing 2, and a stator ring 3. The intermediate casing 2 is installed on the compressor casing 1, and the stator ring 3 is installed inside the compressor casing 1. , the stator ring 3 is provided with stator blades 6 evenly distributed in the circumferential direction, the compressor rotor 4 is located in the compressor casing 1 and is equipped with rotor blades 5, the rotor blades 5 and the stator blades 6 are interlaced to form an inner channel 10, and the intermediate casing 2 The outside is the outer duct 11, which is located at the position of the stator vanes 6 on the stator ring 3. There are radial vent holes 7 in the middle of every two stator vanes 6, and there are holes in the corresponding positions on the compressor casing 1 and the intermediate casing. The diameter is greater than the vent hole 8 of the radial vent hole 7, the number of the stator blades 6 and the radial vent hole is 76, the diameter of the vent hole 7 on the stator ring 3 is 5mm, the compressor casing 1 and the intermediary machine The diameter of the vent hole 7 on the box 2 is 6mm.

Claims (3)

1. aero-engine compressor anti-asthma structure, it is characterized in that, described structure comprises the casing of calming the anger [1], intermediary's casing [] 2 and stator ring [3], intermediary's casing [2] is installed on the casing of calming the anger [1], casing [1] inside of calming the anger is equipped with stator ring [3], stator ring [3] is provided with circumferentially uniform stator blade [6], compressor rotor [4] is positioned at the casing of calming the anger [1] and rotor blade [5] is installed, rotor blade [5] is interlaced with stator blade [6], form main duct [10], intermediary's casing [2] outside is by-pass air duct [11], be positioned at all stator blades [6] position on the stator ring [3], per 2] have radially vent hole [7] in the middle of the sheet stator blade [6], corresponding position has diameter greater than the vent hole [8] of vent hole [7] radially on the casing of calming the anger [1] and intermediary's casing.

2. aero-engine compressor anti-asthma structure as claimed in claim 1 is characterized in that, described stator blade [6] and radially vent hole be 76.

3. aero-engine compressor anti-asthma structure as claimed in claim 1 is characterized in that, the diameter of the vent hole [7] on the described stator ring [3] is 5mm, and the diameter of the vent hole [7] on the casing of calming the anger [1] and the intermediary's casing [2] is 6mm.

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