CN112412864B - Compressor experiment platform and surging and deep stall exit method thereof - Google Patents
Compressor experiment platform and surging and deep stall exit method thereof Download PDFInfo
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- CN112412864B CN112412864B CN202011449693.4A CN202011449693A CN112412864B CN 112412864 B CN112412864 B CN 112412864B CN 202011449693 A CN202011449693 A CN 202011449693A CN 112412864 B CN112412864 B CN 112412864B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
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Abstract
The disclosure relates to a compressor experiment platform and a method for exiting surge and deep stall of the compressor experiment platform. The compressor experiment platform comprises: the inner wall surface of the compressor casing is provided with a plurality of rows of static blades; the compressor hub is arranged inside the compressor casing, the outer wall surface of the compressor hub is provided with a plurality of rows of movable blades, and the upstream fixed blades and the downstream movable blades of adjacent rows form a primary compressor stage; the back pressure valve controls the opening and closing of an outlet of the experimental platform of the gas compressor; and the air entraining assembly is used for carrying out air entraining suction from the outlet of each stage of the compressor at the surge inlet moment. The bleed air subassembly includes: a plurality of rows of air exhaust holes which are arranged on the inner wall surface of the casing of the compressor and are respectively positioned at the outlet of each stage of the compressor; the air guide control valve is arranged on a flow passage path of the air guide hole and used for controlling the opening and closing of the flow passage of the air guide hole; and the suction device is arranged at the outlet of the air guide hole and is used for actively sucking air from the air guide hole to the external atmosphere in a controlled manner. The embodiment of the disclosure can effectively solve the problem of repeated 'surge inlet, surge outlet and surge inlet' in an experimental platform of the gas compressor.
Description
Technical Field
The disclosure relates to the field of aero-engine experiments, in particular to a gas compressor experiment platform and a surging and deep stall exiting method thereof.
Background
Surging is the phenomenon of airflow oscillation with low frequency and high amplitude in the axial direction of the compressor due to the rapid deterioration of a flow field caused by the blade back separation flow of the compressor when the total pressure ratio of the compressor is increased to a certain degree at a certain rotating speed. Stall is a phenomenon of unstable flow field of the compressor due to over-high load, and is usually accompanied by low-energy stall airflow clusters rotating along with the movable blades.
The surge of the compressor can cause great damage to the compressor and even the engine, so that the operation condition of the engine is strictly limited in the normal operation envelope of the engine during the service period of the engine, and the compressor is not allowed to generate surge. In order to accurately obtain the surge boundary of the compressor, in the engine design stage, the engine needs to enter a surge state by increasing the total pressure ratio of the compressor under a series of rotating speeds, so that the surge boundary of the compressor under each rotating speed is obtained.
However, the surge instantaneous energy is huge, and the damage to the compressor is huge, so the duration of the surge state in the test cannot be overlong, and the surge relieving time requirement of the compressor test is usually not more than 0.5 second. Therefore, timely and effective anti-surge measures are of great importance.
However, for surge under a high-rotation-speed and large-working condition, the conventional surge relieving device and method for the experimental platform of the gas compressor can only enable the gas compressor to temporarily exit from a surge state once, and the gas compressor still has a deep stall phenomenon after exiting from the surge state, so that secondary surge of the gas compressor is easily triggered under external extremely small mechanical disturbance, the gas compressor has a repeated phenomenon of 'surge inlet, surge relief, surge inlet', and irreversible damage is brought to experimental parts and the experimental platform of the gas compressor.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide an air compressor experiment platform and a method for exiting surge and deep stall thereof, which can effectively solve the problem of 'surge entering, surge exiting, and surge entering' repeatedly occurring in the air compressor experiment platform, and protect the structure of the air compressor experiment piece and the experiment platform intact.
In one aspect of the present disclosure, a compressor experiment platform is provided, including:
the compressor casing is cylindrical, and the inner wall surface of the compressor casing is provided with a plurality of rows of static blades;
the compressor hub is cylindrical and is rotatably and coaxially arranged in the compressor casing, the outer wall surface of the compressor hub is provided with a plurality of rows of movable blades, and the fixed blades positioned at the upstream and the movable blades positioned at the downstream of the adjacent rows form a first-stage compressor stage;
the back pressure valve is arranged at the outlet of the compressor experiment platform and used for controlling the opening and closing of the outlet of the compressor experiment platform; and
a bleed air assembly configured to draw bleed air from an outlet of each of the compressor stages at a surge transient of the compressor;
wherein the bleed air assembly comprises:
the multiple rows of bleed air holes are formed in the inner wall surface of the compressor casing, and each row of bleed air holes are located on the section of the outlet of each compressor stage one by one so that the outlet of each compressor stage is communicated with the outside atmosphere respectively;
the air guide control valve is arranged on a flow passage path of the air guide hole and used for controlling the opening and closing of the flow passage of the air guide hole, wherein the air guide control valve corresponding to each compressor stage is configured to be kept completely closed in the normal test process, and is completely opened when the compressor is in the surge moment on the basis that the back pressure valve is in the opening state; and
and the suction device is arranged at the outlet of the air guide hole and can actively suck the air from the air guide hole to the external atmosphere in a controlled manner.
In some embodiments, the number of the air holes in each row is 2-4.
In some embodiments, the cross section of the air guide hole on the inner wall surface of the compressor casing is circular, and the aperture of the air guide hole is 0.1-0.2 times of the chord length of the blade tip of the adjacent upstream movable blade.
In some embodiments, the distance between the center of each row of the air guide holes and the tip tail edge of the adjacent upstream bucket is not more than 0.2 times of the tip chord length of the adjacent upstream bucket.
In some embodiments, a trailing edge of each row of the bleed holes is located in an upstream direction from a leading edge of an adjacent downstream vane.
In some embodiments, the bleed control valve is disposed in a position close to an inner wall surface of the compressor casing on a flow path of the bleed hole.
In another aspect of the present disclosure, a method for exiting surge and deep stall of a compressor test platform is provided, which includes the following steps:
opening a back pressure valve at the surge inlet moment of the gas compressor so as to open an outlet of the gas compressor experiment platform;
simultaneously, opening a bleed air control valve in the bleed air assembly to enable an outlet of each stage of the compressor to be communicated with the external atmosphere through a corresponding bleed air hole; and
and controlling a suction device to actively suck the gas from the bleed air hole to the external atmosphere.
In some embodiments, the step of controlling the suction device to actively draw gas from the bleed air port to the external atmosphere comprises:
the method comprises the steps of judging the strength of surge and deep stall while opening a bleed control valve in the bleed air assembly, and controlling a suction device according to the strength of surge and deep stall, so that the suction device actively sucks gas from a bleed hole to the external atmosphere at a proper flow rate.
Therefore, according to the embodiment of the disclosure, the problem of repeated 'surge inlet, surge outlet and surge inlet' in the experimental platform of the compressor can be effectively solved, and the experimental piece and the experimental platform of the compressor are protected to be complete in structure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description, serve to explain the principles of the disclosure.
The present disclosure may be more clearly understood from the following detailed description, taken with reference to the accompanying drawings, in which:
FIG. 1 is a pressure ratio-flow schematic of a surge margin measurement experiment performed by a compressor experiment platform according to some embodiments of the present disclosure;
FIG. 2 is a pressure ratio-flow diagram of a compressor stage at surge and deep stall exit of a compressor test platform according to some embodiments of the present disclosure;
figure 3 is a schematic illustration of a bleed air assembly portion of a compressor test platform according to some embodiments of the present disclosure.
In the figure:
1, a compressor casing; 2, a stationary blade; 3, a compressor hub; 4, moving blades; 5, a gas-guiding assembly; 51, an air guide hole; and 52, introducing the control valve.
It should be understood that the dimensions of the various parts shown in the figures are not drawn to scale. Further, the same or similar reference numerals denote the same or similar components.
Detailed Description
Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and is in no way intended to limit the disclosure, its application, or uses. The present disclosure may be embodied in many different forms and is not limited to the embodiments described herein. These embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that: the relative arrangement of parts and steps, the composition of materials, numerical expressions and numerical values set forth in these embodiments are to be construed as merely illustrative, and not as limitative, unless specifically stated otherwise.
The use of "first," "second," and similar words in this disclosure is not intended to indicate any order, quantity, or importance, but rather is used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element preceding the word covers the element listed after the word, and does not exclude the possibility that other elements are also covered. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
In the present disclosure, when a specific device is described as being located between a first device and a second device, there may or may not be intervening devices between the specific device and the first device or the second device. When a particular device is described as being coupled to other devices, that particular device may be directly coupled to the other devices without intervening devices or may be directly coupled to the other devices with intervening devices.
All terms (including technical or scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs unless specifically defined otherwise. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate.
The applicant researches and discovers that: in the existing compressor part test, a commonly used method for relieving surge mainly comprises the steps of adjusting a back pressure valve at the outlet of a compressor, increasing the area of the outlet of the compressor, and reducing the total pressure ratio of the compressor to enable the compressor to be out of a surge state. The surge relieving method can effectively relieve surge of the compressor with medium and low rotating speeds, but test practices show that the following problems exist in the high-rotating-speed and large-working-condition state of the compressor.
Firstly, because the compressor has huge energy at the surge inlet moment, the surge relieving method for adjusting the back pressure valve at the outlet of the compressor can only enable the compressor to temporarily quit the surge state once, and the phenomenon of deep stall is still accompanied after the compressor quits the surge state. Due to the existence of the deep stall phenomenon, the secondary surge of the compressor can be triggered by the tiny external mechanical disturbance, and the phenomenon of 'surge entrance, surge retreat, surge entrance' of the compressor is caused repeatedly.
Secondly, when the compressor has the phenomena of 'surge inlet, surge outlet and surge inlet' under the condition of high rotating speed and large working condition, the traditional surge outlet method can only adopt the emergency rotation reduction measure. And the emergency rotation-down action easily causes a series of mechanical problems of angle non-following of the adjustable stator blade (VSV), angle locking of the adjustable stator blade, tripping of a motor and the like, and secondary damage is brought to a gas compressor test piece and a test bed.
In view of this, as shown in fig. 1 to 3, in order to avoid the problem of repeated "advance surge, retreat surge, advance surge" easily caused by the conventional surge retreating method, and avoid mechanical secondary damage of the experimental part and the experimental platform of the compressor induced by the emergency drop measure, in one aspect of the present disclosure, a compressor experimental platform is provided, which includes:
the compressor casing 1 is cylindrical, and the inner wall surface of the compressor casing is provided with a plurality of rows of static blades 2; and
the compressor hub 3 is cylindrical, is rotatably and coaxially arranged in the compressor casing 1, and is provided with a plurality of rows of movable blades 4 on the outer wall surface;
wherein, the stator blade 2 that is located the upper reaches of adjacent row and the movable blade 4 that is located the low reaches constitute first-order compressor stage, and compressor experiment platform still includes:
and the bleed air assembly 5 is configured to suck bleed air from the outlet of each stage of the compressor at the surge instant of the compressor.
The compressor casing 1 and the rows of stationary blades 2 arranged thereon together form a stator part of the compressor, and the compressor hub 3 and the rows of movable blades 4 arranged thereon together form a rotor part of the compressor. In the working process of the experimental platform of the gas compressor, the rotor part of the experimental platform can be driven by a rotating shaft driven by a motor or a turbine, and further the gas working medium flowing through the experimental platform is accelerated and pressurized through the rotation motion; the stator part is static relative to the ground, aiming at adjusting the moving direction of the gas working medium to adapt to the attack angle requirement of the adjacent movable blades 4 at the downstream.
Each compressor stage is composed of a row of static blades 2 and a row of movable blades 4 distributed along the circumferential direction, the static blades 2 are arranged to enable the flow direction of a gas working medium flowing along the axial direction to be adjusted to be suitable for the rotating movable blades 4, the flow direction of the gas working medium flowing through the rotating movable blades 4 returns to the axial direction again, and the gas working medium enters the next compressor stage, so that the compressor stages with the static blades 2-the movable blades 4 as a unit are circularly arranged along the axial direction, and the multistage axial flow compressor is formed.
Aiming at the surge problem under the environment, particularly the surge problem under the high-rotating-speed and large-working-condition state, the air-entraining component 5 is arranged on the section of the outlet of each stage of the compressor, and the low-energy fluid mass with surging or deep stall at the blade tip of the outlet of the rotor of each stage of the compressor is pumped away, so that the flow quality of the flow field of the compressor is improved.
In the surge relieving scheme in the prior art, by opening a back pressure valve at the outlet of the compressor, bleed air suction at the outlet of the compressor or bleed air suction at the outlets of a plurality of specific compressor stages in the compressor is realized, so that the compressor can relieve the surge integrally. However, the compressor stages that are not bled still remain in the same aerodynamic environment as the surge condition, with low energy stall clusters rotating with the rotor, and are therefore susceptible to minor mechanical or aerodynamic disturbances, such as vibration of the body or minor changes in the compressor inlet conditions, to re-trigger secondary surge of the compressor.
The bleed air suction is carried out on the outlet section of each stage of the compressor stage, and the low-energy fluid mass at the movable blades 4 of each stage of the compressor stage is sucked away, so that the flow quality of the interior of the compressor, particularly the pneumatic environment where the movable blades 4 are located, is fundamentally changed, and the pneumatic working condition of triggering surge is far away from the single-stage compressor stage and the whole compressor.
The principle is as follows: the bleed air suction at the outlet of each stage of compressor also increases the outlet area of the single-stage compressor and reduces the single-stage load, as shown in fig. 2, the bleed air suction at the outlet of the single-stage compressor makes each stage of compressor develop toward a blockage point along a single-stage characteristic line, so that the operating condition is far away from a surge point, and the sucked low-energy fluid mass also makes the compressor effectively exit from a deep stall state, so that any stage of compressor is not easily affected by mechanical or pneumatic disturbance due to stall and suffers from surge again.
For those skilled in the art, the above-mentioned anti-surge scheme can also be applied to a centrifugal compressor that enters into a surge state due to a high-speed and high-operating condition, and the principle thereof is similar to the anti-surge principle of the present disclosure, and will not be described herein again.
In some embodiments, the compressor experiment platform further comprises: and the back pressure valve is arranged at the outlet of the compressor experiment platform and used for controlling the opening and closing of the outlet of the compressor experiment platform. As shown in fig. 3, in some embodiments the bleed air assembly 5 comprises:
a plurality of rows of air guide holes 51 arranged on the inner wall surface of the compressor casing 1, wherein each row of air guide holes 51 is positioned on the section of the outlet of each compressor stage one by one, so that the outlet of each compressor stage is respectively communicated with the outside atmosphere; and
the air-bleed control valve 52 is provided in the flow path of the air-bleed hole 51, and controls opening and closing of the flow path of the air-bleed hole 51. The pilot control valve 52 for each of the compressor stages may remain fully closed during normal testing and fully open at the surge transient of the compressor based on the back pressure valve being open.
The air guide hole 51 is formed in the inner wall surface of the compressor casing 1, so that the air flow at the outlet of each stage of the compressor can directly enter the atmosphere through the air guide hole 51. Of course, it is obvious to those skilled in the art that the bleed holes 51 may be provided on the compressor hub 3 side so that each compressor stage exhausts air radially inward and communicates with the outside atmosphere through a bleed line provided inside the compressor hub 3.
The bleed control valve 52 may be a flow control valve such as a throttle valve or a governor valve, and controls opening and closing of the flow passage of the bleed hole 51.
Because the gas working medium flowing through the gas compressor can improve the pressure of the gas working medium under the action of the rotation of the gas compressor, and the inlet pneumatic working condition of the experimental platform of the gas compressor is a normal-temperature normal-pressure environment, the automatic exhaust from the stage outlets of the gas compressors to the outside atmosphere can be automatically realized by depending on the pressure difference that the gas working medium in the gas compressor is higher than the ambient gas.
Generally, the experimental surge relief time requirement of the compressor is not more than 0.5 second, so in order to meet the surge relief time requirement, the speed of bleed air suction is increased and controlled, and in some embodiments, the bleed air assembly 5 further comprises:
and a suction device which is arranged at the outlet of the air guide hole 51 and can actively suck air from the air guide hole 51 to the external atmosphere in a controlled manner.
Based on the arrangement of the suction device, when the surge enters the air compressor experiment platform, the active suction intensity of the suction device can be selected according to the working condition of the air compressor or the surge intensity during the surge entering, so that the air entraining assembly 5 can form adaptive intensity adjustment relative to the surge intensity, and the surge phenomenon under different working conditions and different intensities can be better coped with.
In the embodiment, the air guide holes are formed in the outlets of the compressor stages of each stage, and the air guide control valves and the suction devices are used for pneumatic control, so that the surge boundary of the compressor can be widened, the stability of the compressor in high rotating speed and large working conditions is improved, the adaptability of the aircraft engine to different working conditions is greatly improved, the accident rate of the aircraft engine in extreme working conditions is integrally reduced, and the overall safety of the aircraft is improved.
Because the flow condition of the boundary layer at the wall surface of the compressor has great influence on the pneumatic organization in the compressor, and the air guiding holes 51 are formed in the inner wall of the compressor casing 1, the disturbance effect of the formation of the air guiding holes 51 on the air flow in the compressor is considered.
Based on this, in some embodiments, the number of the exhaust holes 51 per row is 2 to 4. The applicant researches and discovers that when the number of each row of bleed air holes 51 is limited to 2-4, the bleed air holes 51 can not only meet the requirement of leading out enough stall air masses, but also can not generate a large turbulent flow effect on a flow field in the compressor, and can still maintain the normal pneumatic operation of a downstream compressor stage.
Furthermore, in consideration of the pressure ratio of each compressor stage and the flow requirement of the active suction gas, under the limitation of the number of the 2-4 bleed holes 51 in each row, the cross section of the bleed hole 51 on the inner wall surface of the compressor casing 1 is circular, and the aperture of the bleed hole 51 is 0.1-0.2 times of the chord length of the blade tip of the adjacent upstream movable blade 4.
In order to reduce the influence of the bleed holes 51 on the upstream and downstream two-stage compressor stages and enable the holes of the bleed holes 51 on the wall surface of the compressor casing 1 to be right opposite to the positions of the stall air masses when surge occurs, in some embodiments, the distance from the center of each row of the bleed holes 51 to the tip tail edge of the adjacent upstream movable blade 4 is not more than 0.2 times of the tip chord length of the adjacent upstream movable blade 4. And the trailing edge of each row of the introducing holes 51 is located in the upstream direction of the leading edge of the adjacent downstream vane 2.
Since the opening or closing of the bleed hole 51 is controlled by the bleed control valve 52, the position at which the bleed control valve 52 is disposed will affect the effective depth of the bleed hole 51 in the closed state. In view of the above, the applicant has found that the smaller the effective depth of the bleed holes 51 in the closed state has the more limited influence on the aerodynamics inside the compressor, and therefore, in order to further reduce the disturbance of the bleed holes 51 on the gas flow pattern inside the compressor, in some embodiments, the position of the bleed control valve 52 on the flow path of the bleed holes 51 is close to the inner wall surface of the compressor casing 1.
In another aspect of the present disclosure, a method for exiting surge and deep stall of a compressor test platform is provided, which includes the following steps:
opening a back pressure valve at the surge inlet moment of the gas compressor so as to open an outlet of the gas compressor experiment platform;
simultaneously, opening a bleed control valve 52 in the bleed assembly 5 to enable the outlet of each compressor stage to be communicated with the external atmosphere through a corresponding bleed hole 51; and
the suction means is controlled to actively suck gas from said bleed holes 51 to the outside atmosphere.
Specifically, in the normal test process, the bleed air control valve 52 is kept fully closed, and only at the surge inlet moment of the compressor when the surge boundary measurement test of the compressor is carried out, the surge-relieving bleed air valve behind each stage of the rotor is instantly and fully opened on the basis of opening the back pressure valve at the outlet of the compressor, so that low-energy fluid mass at the surge inlet moment is sucked. By the method, the phenomenon of deep stall can be effectively avoided, the phenomenon of repeated 'surge inlet, surge outlet and surge inlet' of the gas compressor is avoided, and the effective surge outlet of the gas compressor is realized.
In some embodiments, the step of controlling the suction device to actively suck the gas from the gas guiding hole 51 to the outside atmosphere comprises:
the strength of surge and deep stall is determined at the same time as the bleed control valves 52 in the bleed air assemblies 5 are opened, and the suction device is controlled in dependence on the strength of surge and deep stall so that the suction device actively sucks gas from the bleed air holes 51 to the outside atmosphere at a suitable flow rate.
Therefore, according to the embodiment of the disclosure, the problem of repeated 'surge entering, surge withdrawing and surge entering' in the conventional compressor surge withdrawing method can be effectively solved, and the surge/deep stall state can be effectively withdrawn without implementing emergency drop measures;
because the implementation of an emergency drop-off measure is avoided, mechanical problems such as no following of an adjustable stator blade, tripping of a motor and the like can be avoided, and secondary damage to a gas compressor test piece and a gas compressor test bed can be avoided;
because the surge can be timely relieved, the surge state is maintained for a short time, the damage to the hardware of the air compressor is minimized, and the safety of the test is ensured to the greatest extent.
Thus, various embodiments of the present disclosure have been described in detail. Some details well known in the art have not been described in order to avoid obscuring the concepts of the present disclosure. It will be fully apparent to those skilled in the art from the foregoing description how to practice the presently disclosed embodiments.
Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the foregoing examples are for purposes of illustration only and are not intended to limit the scope of the present disclosure. It will be understood by those skilled in the art that various changes may be made in the above embodiments or equivalents may be substituted for elements thereof without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.
Claims (8)
1. An experimental platform for a gas compressor, comprising:
the compressor casing (1) is cylindrical, and the inner wall surface of the compressor casing is provided with a plurality of rows of static blades (2);
the compressor hub (3) is cylindrical and is rotatably and coaxially arranged in the compressor casing (1), the outer wall surface of the compressor hub is provided with a plurality of rows of movable blades (4), and the fixed blades (2) positioned at the upstream and the movable blades (4) positioned at the downstream of the adjacent rows form a primary compressor stage;
the back pressure valve is arranged at the outlet of the compressor experiment platform and used for controlling the opening and closing of the outlet of the compressor experiment platform; and
a bleed air assembly (5) configured to draw bleed air from the outlet of each of said compressor stages at a surge instant of the compressor; wherein the bleed air assembly (5) comprises:
a plurality of rows of air-bleed holes (51) which are arranged on the inner wall surface of the compressor casing (1), wherein each row of air-bleed holes (51) is positioned on the section of the outlet of each compressor stage one by one, so that the outlet of each compressor stage is respectively communicated with the external atmosphere;
the bleed control valve (52) is arranged on a flow path of the bleed hole (51) and used for controlling the opening and closing of the flow path of the bleed hole (51), wherein the bleed control valve (52) corresponding to each compressor stage is configured to be kept fully closed in the normal test process, and is fully opened when the compressor is in the surge moment on the basis that the backpressure valve is in the opening state; and
and a suction device which is arranged at the outlet of the air guide hole (51) and can actively suck the gas from the air guide hole (51) to the external atmosphere in a controlled manner.
2. The compressor experiment platform as claimed in claim 1, wherein the number of the air guide holes (51) in each row is 2-4.
3. The compressor experiment platform as claimed in claim 1, wherein the cross section of the air guide hole (51) on the inner wall surface of the compressor casing (1) is circular, and the aperture of the air guide hole (51) is 0.1-0.2 times of the chord length of the blade tip of the adjacent upstream movable blade (4).
4. The compressor experiment platform as claimed in claim 3, wherein the distance from the center of each row of the air guide holes (51) to the tip tail edge of the adjacent upstream movable blade (4) is not more than 0.2 times of the tip chord length of the adjacent upstream movable blade (4).
5. An experimental compressor platform according to claim 4, characterized in that the trailing edge of each row of the air guiding holes (51) is located in the upstream direction of the leading edge of the adjacent downstream vane (2).
6. Compressor laboratory platform according to claim 1, characterized in that the bleed air control valve (52) is arranged close to the inner wall surface of the compressor casing (1) in the flow path of the bleed air hole (51).
7. A method for exiting surge and deep stall of an experimental platform of a compressor is characterized in that the experimental platform of the compressor comprises the following steps: the device comprises a compressor casing (1), a compressor hub (3), a back pressure valve and an air-entraining component (5); wherein, the inner wall surface of the compressor casing (1) is provided with a plurality of rows of stationary blades (2); the compressor hub (3) is rotatably and coaxially arranged inside the compressor casing (1), the outer wall surface of the compressor hub is provided with a plurality of rows of movable blades (4), and the fixed blades (2) positioned at the upstream and the movable blades (4) positioned at the downstream of the adjacent rows form a first-stage compressor stage; the back pressure valve is arranged at the outlet of the compressor experiment platform; the bleed air assembly (5) further comprising a plurality of rows of bleed air holes (51) and a bleed air control valve (52); the multiple rows of air guide holes (51) are formed in the inner wall surface of the compressor casing (1), and each row of air guide holes (51) are located on the outlet section of each compressor stage one by one; the air-introducing control valve (52) is arranged on a flow path of the air-introducing hole (51);
the method for exiting the surge and deep stall of the compressor experiment platform comprises the following steps:
opening a back pressure valve at the surge inlet moment of the gas compressor so as to open an outlet of the gas compressor experiment platform;
simultaneously, opening a bleed control valve (52) in the bleed assembly (5) to enable the outlet of each compressor stage to be communicated with the external atmosphere through a corresponding bleed hole (51); and
controlling the suction device to actively suck gas from the gas guiding hole (51) to the external atmosphere.
8. The method of exiting surge and deep stall according to claim 7, wherein the step of controlling the suction means to actively suck gas from said bleed holes (51) towards the outside atmosphere comprises:
simultaneously with opening the bleed control valve (52) in the bleed air assembly (5), the strength of surge and deep stall is determined and the suction device is controlled in dependence on the strength of surge and deep stall so that it actively draws gas from the bleed orifice (51) to the outside atmosphere at a suitable flow rate.
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| CN102177347A (en) * | 2008-10-13 | 2011-09-07 | 拓博有限公司 | Blow-off system for multi-stage turbo compressor |
| JP6045732B1 (en) * | 2016-02-10 | 2016-12-14 | シグマ紙業株式会社 | Container holder |
| CN108518355A (en) * | 2018-03-22 | 2018-09-11 | 清华大学 | A kind of reshaping compressor pumping casing |
| CN109838313A (en) * | 2019-03-29 | 2019-06-04 | 国电环境保护研究院有限公司 | A kind of gas turbine anti-asthma blow-off system |
| CN111927819A (en) * | 2020-10-15 | 2020-11-13 | 中国航发上海商用航空发动机制造有限责任公司 | Combined anti-surge method and multistage axial flow compressor experiment platform |
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| JPS6045732A (en) * | 1983-08-24 | 1985-03-12 | Nissan Motor Co Ltd | Device for avoiding surge in gas turbine engine |
| JP3322633B2 (en) * | 1998-04-20 | 2002-09-09 | 三菱重工業株式会社 | Bleed air flow control system for axial compressor |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102177347A (en) * | 2008-10-13 | 2011-09-07 | 拓博有限公司 | Blow-off system for multi-stage turbo compressor |
| JP6045732B1 (en) * | 2016-02-10 | 2016-12-14 | シグマ紙業株式会社 | Container holder |
| CN108518355A (en) * | 2018-03-22 | 2018-09-11 | 清华大学 | A kind of reshaping compressor pumping casing |
| CN109838313A (en) * | 2019-03-29 | 2019-06-04 | 国电环境保护研究院有限公司 | A kind of gas turbine anti-asthma blow-off system |
| CN111927819A (en) * | 2020-10-15 | 2020-11-13 | 中国航发上海商用航空发动机制造有限责任公司 | Combined anti-surge method and multistage axial flow compressor experiment platform |
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