CN114562472A

CN114562472A - Compressor test structure

Info

Publication number: CN114562472A
Application number: CN202111366064.XA
Authority: CN
Inventors: 王士奇; 闫昭琦; 陈前景; 贾志刚; 潘天宇
Original assignee: China Aero Engine Research Institute
Current assignee: China Aero Engine Research Institute
Priority date: 2021-11-18
Filing date: 2021-11-18
Publication date: 2022-05-31
Anticipated expiration: 2041-11-18
Also published as: CN114562472B

Abstract

The invention provides a gas compressor testing structure. The structure main body is a rotor casing, connection with an air inlet cone and the stator casing is achieved, meanwhile, due to the fact that the exciter mounting ring and the rotor casing are arranged in a separated mode, the relative position of the exciter mounting ring and the rotor casing can be flexibly adjusted, and therefore the position of the exciter can be adjusted. The exciter mounting ring is also provided with an exciter mounting groove which is fixedly connected with the exciter and/or the baffle, so that the baffle can be matched with the exciter under the condition of not changing the exciter mounting ring to form tests with different numbers of exciters, and the cost and the test period are further reduced.

Description

Compressor test structure

Technical Field

The invention belongs to the field of aviation gas turbines, and particularly relates to a measuring method and a structure of an active control stability expansion measure in an aviation gas turbine engine. The invention particularly relates to a design scheme of an active stability augmentation test structure based on a high-frequency oscillation ejector, which is mainly used for quantitatively researching the stability augmentation capability and generation mechanism of the active jet type oscillator on an aviation compressor under multiple parameters.

Background

The fan/compressor is one of the main components of the aircraft engine/gas turbine engine, and the development of a high-performance fan and an axial flow compressor is a key problem in the design of the modern aircraft engine/gas turbine engine. However, the pursuit of high pressure ratios in compressor design, meaning higher tip tangential velocities, larger turning angles and smaller blade aspect ratios, all increase flow losses within the compressor, thereby affecting the efficiency and stable operating margins of the compressor. This leads to a set of key contradictions in the development of the compressor, which also ensures high working stability and wide enough stall margin under the conditions of ensuring high speed and high pressure ratio. The solution to this conflict is to adopt a flow control method.

The flow control method mainly comprises a passive flow control technology and an active flow control technology. The effective range of the passive flow control technology is limited, the defect that the passive flow control technology cannot be adjusted according to actual working conditions exists during working, the control effect is easily influenced by the change of the flow state, extra additional resistance can be brought under the non-design state, and the original pneumatic performance is reduced. Compared with passive control, active flow control is a control method for introducing flow by auxiliary energy, and is characterized in that appropriate disturbance is directly injected in a flow environment to enable the disturbance to generate certain interaction with the flow in a system so as to achieve the control purpose, and the control characteristic of the active flow control can be subjected to self-adaptive adjustment and control according to the actual situation. External disturbance and energy injection are required to be introduced for active flow control, and compared with a steady-state blowing/inhaling method, the active flow control method based on periodic unsteady-state excitation is higher in efficiency and calculated by adding a momentum coefficient, the efficiency can be improved by two orders of magnitude, and the method is verified in application research in various fields. These periodic unsteady-state perturbations are generated by a variety of actuators, with synthetic jet actuators, plasma actuators, fluidic oscillators, and the like being more typical. However, the operating conditions in the aircraft engine are severe, the reliability requirements on all parts are extremely high, and the difficulty of using unsteady flow control is lack of an exciter with simple structure and high reliability.

A fluidic oscillator is an active control device that inputs a source of gas at a given pressure at an inlet and produces a periodic oscillating jet at an outlet. The device has the advantages of no movable part, simple structure, large flow quantity at the outlet, self-oscillation, self-excitation maintenance and the like, thereby greatly arousing the interest of researchers. The design key points are mainly two: one is the coanda effect, i.e. the coanda effect of a fluid; and the other is a feedback channel, namely when the fluid is attached to one side wall surface, part of the fluid flows out from the outlet, the other part of the fluid flows back to the outlet along the feedback channel, a separation packet is generated between the main flow and the wall surface under the action of the fluid flowing back in the feedback channel, and the separation packet can force the main flow to the other side wall surface until the main flow is attached to the other side wall surface. The two points make the main flow in the mixing cavity attach to the two side wall surfaces back and forth, so that the jet flow with the periodically oscillating outlet is generated. At present, the method is mainly applied to the aspects of controlling the separation of a wing boundary layer, improving the lift force of an airplane, enhancing the mixing in a combustion chamber, cooling a gas mould of a gas turbine blade, suppressing noise and the like.

At present, the test and analysis of the jet oscillator are more applied to outflow, however, for the control problem in the aspect of flow separation inside the compressor, the application and test scheme of the jet oscillator still needs to be further improved. Due to the small size of the outlet of the fluidic oscillator itself, the area of influence is limited, whereas the area to be controlled is generally large in comparison. In order to apply fluidic oscillators to practical flow separation control scenarios, a series of fluidic oscillator arrays need to be arranged within the flow area to be controlled. Thus, a series of discrete periodic oscillating jet excitations are formed at the surface of the controlled area. The outlet of the oscillating jet is arranged at the leading edge of the flow separation to delay or eliminate the occurrence of the flow separation. Meanwhile, the design of the internal flow channel of the fluid oscillator, the wall surface of the air inlet cone and the air compressor/turbine casing is combined, a high-pressure air source is introduced from the external or the back-stage air compressor, and the required oscillating jet flow working frequency and amplitude are formed at the outlet of the oscillator by adjusting the pressure at the inlet of the flow channel of the fluid oscillator, so that the working efficiency, the working margin and the overall performance of the engine can be greatly improved on the premise of not increasing the complexity of the existing structure and not reducing the reliability and the safety of the existing gas turbine engine. The flow separation active control technology in the aircraft engine based on the self-excited oscillation jet flow combines the advantages of high active flow control efficiency and high reliability/safety of passive flow control, and obtains a good effect of active control in a passive control mode. The method is applied to an air inlet cone, an air compressor and a turbine, can obviously improve the working efficiency, the working margin and the overall performance of the aircraft engine, simultaneously considers the safety, the reliability and the complexity of a system structure, and has wide prospect in the practical engineering application.

The active adjusting effect of the stability margin of the gas compressor is closely related to the jet flow excitation position, the excitation angle, the distribution position of the exciters, the number of the exciters, the speed and the frequency of the excitation jet flow. However, once the design geometry of the fluidic oscillator is determined, the frequency response characteristic and the speed response characteristic of the fluidic oscillator along with the change of the inlet pressure are also determined when the working medium characteristic is not changed. The excitation speed and frequency can only be adjusted by adjusting the inlet pressure. In order to quantitatively research the influence of the different excitation parameters on the active stability expansion of the gas compressor, a large amount of parametric experimental research needs to be carried out, and besides the excitation speed and the frequency, the influence also comprises the influence of the jet excitation position, the excitation angle, the number of the exciters and the distribution position of the exciters. Each group of parameter combination requires a plurality of complex flow channels of the fluidic oscillator to be processed on the annular compressor casing, which results in excessively high test cost and excessively long test period.

Disclosure of Invention

In order to solve at least one of the above technical problems, the invention provides a gas compressor test structure, which can reduce the cost and the period of experimental research, and based on the selected jet type high-frequency oscillator, a variable-parameter gas compressor active stability expansion test structure needs to be designed, so as to conveniently, quickly and low-cost research on a multi-parameter stability expansion mechanism based on unsteady-state blade tip micro-jet excitation of a fluid oscillator. The purpose of the invention is realized by the following scheme:

a compressor testing structure comprises a rotor case, an exciter mounting ring and a fixing part, wherein the rotor case is fixedly connected with an air inlet cone and a stator case respectively, and a plurality of first through holes are formed in the rotor case; the exciter mounting ring is provided with a plurality of exciter mounting grooves which correspond to the first through holes and are arranged at an angle, and the mounting grooves are arranged in a penetrating manner; the exciter mounting ring is coaxially connected with the rotor casing, and the rotor casing is fixedly connected with the exciter mounting ring through the fixing part; the exciter mounting groove is adapted to be fixedly connected with an exciter and/or a baffle.

The exciter mounting seat is provided with a first fixing area fixed with the exciter mounting ring, a second fixing area used for fixing with an exciter, and a second through hole suitable for being communicated with the exciter mounting groove, and the second through hole is also suitable for being inserted into the exciter.

Further, the first through hole and the exciter mounting groove are inclined at the same angle, and the angle between the inclination angle and the axis of the rotor casing is not larger than 30 degrees.

Further, the included angle is 25 °.

Further, the width of the exciter mounting groove corresponds to the thickness of the exciter outlet portion.

Furthermore, threaded holes are formed in two sides of the exciter mounting groove, the first fixing area is a through hole penetrating through the upper surface and the lower surface of the exciter mounting seat, and the through hole of the first fixing area corresponds to the threaded holes.

Further, an outlet of the second through hole close to the axis of the rotor case is provided with a fillet.

Furthermore, the exciter mounting ring is also provided with a mounting hole for mounting a pressure pulsation sensor.

Further, a plurality of millimeter-sized small holes are machined in the circumferential direction of the rotor casing in an equal division mode, and the small holes are used for installing sensors for measuring rotor blade tip disturbance.

Furthermore, the fixed part comprises a plurality of positioning rings, the first through hole is a rectangular through hole, the long edge of the first through hole is parallel to the axis of the rotor casing, the positioning rings are used for adjusting the position of the exciter mounting ring, and the exciter mounting groove moves in the corresponding range of the first through hole.

Further, the nozzle aerodynamic range of the exciter is-0.4 c to 0.2c, wherein c is the rotor tip chord length.

Further, the nozzle of the exciter is respectively positioned at the positions-0.4 c, -0.2c, 0c and 0.2c away from the front edge of the rotor, wherein c is 118mm-120 mm.

Compared with the prior art, the invention has the advantages that: the invention provides a gas compressor testing structure. The rotor casing is connected with the air inlet cone and the stator casing, and the exciter mounting ring and the rotor casing are arranged in a separated mode, so that the positions of the exciter mounting ring and the rotor casing can be flexibly adjusted, the position of the exciter is adjusted, the exciter mounting ring and the rotor casing are designed in a separated mode, and the exciter mounting ring can be replaced according to different requirements, so that the mounting angle of the exciter, the number of the exciters and the like can be changed. The exciter mounting ring is also provided with an exciter mounting groove which is fixedly connected with the exciter and/or the baffle, so that the baffle can be matched with the exciter to form tests with different numbers of exciters under the condition of not changing the exciter mounting ring, and the cost and the test period are further reduced.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the principles of the invention.

FIG. 1 is a schematic view of the assembly of a compressor test structure and an inlet cone of the present invention;

FIG. 2 is an axial cross-sectional view of the assembled structure of FIG. 1;

FIG. 3 is a schematic view of a compressor test structure mounting actuator;

FIG. 4 is a schematic view of the rotor case of FIG. 2;

fig. 5 is a schematic view of fig. 3 with the exciter and baffle installed simultaneously.

FIG. 6 is a schematic view of the exciter mount ring of FIG. 2;

FIG. 7 is a first schematic view of the exciter mount of FIG. 2;

FIG. 8 is a second schematic view of the exciter mount of FIG. 2;

FIG. 9 is two configurations of a pulsed fluidic oscillator;

FIG. 10 is a typical velocity response plot for a pulsed fluidic oscillator outlet.

Fig. 11 is a schematic view of a swept jet ejector.

Wherein: 100. an air inlet cone; 200. a compressor testing structure; 210. a rotor case; 211. a case body; 212. a first flange; 213. a second flange; 214. a first through hole; 220. an exciter mount ring; 221. a mounting ring body; 222. an exciter mounting groove; 223. a threaded hole; 230. a fixed part; 240. an exciter mount; 241. a second through hole; 242. a first fixing region; 243. a second fixation area; 244. a mounting surface; 250. a baffle plate; 300. an exciter.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.

In addition, the embodiments of the present invention and the features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

Referring to the specification and to fig. 1, the present invention provides a compressor test structure 200, the test structure 200 adapted to interface with an inlet cone 100 such that a rotor portion enters the test structure.

Fig. 2 shows the specific case of the test structure 200 interfacing with an inlet cone. The test structure 200 includes a rotor case 210, an exciter mount ring 220, and a stationary portion.

The rotor casing 210 is fixedly connected with the air inlet cone 100 respectively, the rotor casing 210 is firstly matched with the upstream air inlet cone 100 and the downstream stator casing, and the interface adopts a spigot design to ensure the sealing performance after matching. Referring to fig. 4, the rotor casing 210 includes a casing body 211, a first flange 212, a second flange 213, and a first through hole 214. The first flange 212 and the second flange 213 are sandwiched between two sides of the casing body 211. The first flange 212 is used for being butted with the air inlet cone 100, and the second flange 213 is used for being butted with a stator casing. The first flange 212 is provided with a step corresponding to the inlet cone 100, i.e. a spigot design. The sealing between the inlet cone 100 and the rotor casing 210 is achieved by the above-mentioned spigot. The first flange 212 is provided with locking holes which are uniformly distributed, the air inlet cone 100 is provided with threaded holes or unthreaded holes corresponding to the locking holes, and the locking connection of the structures is realized through bolts. The second flange 213 is also provided with a locking hole for locking with the stator case. The middle of the casing body 211 is provided with a first through hole 214. The exciter 300 is able to direct an exciting jet to the rotor blade through the first through hole 214. In a preferred embodiment, in order to avoid stress concentration, the first through hole 214 is a rectangular through hole, and a chamfered structure is adopted at a right-angled portion of the rectangular through hole. And after casting is finished, the internal stress of the material is further eliminated, and the strength of the test piece is ensured. The rotor case 210 is also perforated with a rectangular number of holes at equal intervals when the maximum number of exciters are mounted in the circumferential direction of the exciter 300. In addition, not less than 6 small holes with two millimeters are machined in the circumferential direction in an equal dividing mode, so that a dynamic Kulett sensor can be installed in the experiment process to measure the disturbance development evolution of the rotor blade tip. The rotor casing 210 is also provided with a positioning boss, which is preferably provided close to the side of the inlet cone 100 with the first through hole 214.

The exciter mounting ring 220 is adapted to abut the locating boss, thereby forming a location for the exciter mounting ring 220. In a preferred embodiment, the exciter mounting ring 220 is disposed inside the rotor casing 210 and coaxially connected to the rotor casing 210. At this time, the fixing portion 230 is also disposed inside the rotor case 210, thereby locking and positioning the exciter mounting ring 220. The present invention does not exclude the solution of disposing the exciter mounting ring 220 outside the rotor casing 210, and when the exciter mounting ring 220 is disposed outside the rotor casing 210, the positioning boss is disposed on the outer side of the casing body 211, and the fixing portion 230 is also disposed on the outer side of the rotor casing 210. In a preferred embodiment, the fixing portion 230 includes positioning rings, the first through hole 214 is a rectangular through hole, the long side of the first through hole 214 is parallel to the axis of the rotor casing 210, the positioning rings are used for adjusting the position of the exciter mounting ring 220, and the exciter mounting groove 222 moves within the corresponding range of the first through hole 214. Specifically, the positions of the exciter mounting ring 220 and the positioning rings may be adjusted, and the positioning rings are disposed at the front and rear ends of the exciter mounting ring 220, and the positioning rings abut against the positioning bosses. According to different installation sequences, the change of the axial position of the exciter 300 can be realized by adjusting the axial position of the exciter installation ring 220, so that the change of the stability expanding capability of the exciter 300 on the compressor under the change of the axial position is researched. Since the change in the axial position of the exciter mounting ring 220 necessarily causes a change in the relative position between the exciter mounting groove 222 and the first through hole 214, in order to always expose the exciter mounting groove 222 in the area of the first through hole 214, the first through hole 214 is a rectangular through hole, and the long side of the first through hole 214 is parallel to the axis of the rotor case 210.

Because the final instability of the compressor is caused by the disturbance of the rotor blade tip, the nozzle of the exciter can be positioned at different axial positions of the rotor casing through the positioning ring. After the exciter positioning ring is installed in the rotor casing 210, the inner wall surface of the rotor casing 210 has a portion of the axial length, which is filled with the positioning ring. And the remaining length is divided equally to produce rings of the same size, and the axial position of one or more of the positioning rings and the exciter mounting ring 220 is adjusted on the basis of the positioning. Axial movement of the exciter 300 is achieved by adjusting the axial mounting sequence to be different from that of the exciter mounting ring 220 relative to the rotor case 210. The selection of the size ensures that the exciter 300 can move axially within a range of-0.4 c to 0.2c, wherein c is the chord length of the rotor blade tip. In this embodiment, the orifices of the actuator are located-0.4 c, -0.2c, 0c, 0.2c from the leading edge of the rotor, where c is 118mm-120mm, respectively, based on the particular width of the positioning ring.

Referring to fig. 6, the exciter mounting ring 220 includes a mounting ring body 221 and an exciter mounting groove 222. The exciter mounting grooves 222 are uniformly distributed along the annular surface of the mounting ring body 221. The exciter mount 240 corresponds in position to the first through hole 214 and is angled. To avoid affecting the main flow development and disturbing the radial propagation, the angle of inclination should be no more than 30 ° from the axis of the casing. In this embodiment, actuator mounting slots 222 that are 25 ° open on the inner ring are ultimately defined by iterative design adjustments for the mounting of the fluidic actuator. The exciter mount groove 222 is a rectangular hole parallel to the wall surface of the exciter 300, so that the outlet air flow is not structurally affected.

Further, the width of the exciter mounting groove 222 corresponds to the thickness of the outlet portion of the exciter 300. Thereby not affecting the air outlet of the ejector. Referring to fig. 3, the width of the exciter mounting groove 222 is a dimension of the rectangular groove perpendicular to the plane direction of the bottom of the exciter mounting groove 222. The number of exciter mounting grooves 222 on the exciter mounting ring 220 corresponds to the maximum number of exciters that can be mounted on the rotor casing 210 in the circumferential direction, and it is also required that the number of exciters 300 is uniformly distributed on the rotor casing 210 in the circumferential direction, and when the number of exciters 300 is less than the maximum number of exciters, the empty space is blocked by the blocking plate 250.

In addition, two-millimeter screw holes 223 are formed on both sides of each rectangular hole on the outer wall surface of the exciter mount ring 220 to be engaged with the exciter mount 240. Two mounting holes as shown in fig. 6 are simultaneously machined axially to measure pressure pulsations for subsequent mounting of the dynamic sensor.

Referring to fig. 7-8, when the exciter 300 is mounted to the exciter mount ring 220 at the same inclination angle, the upper surface of the exciter extends beyond the outer surface of the exciter mount ring 220, resulting in the exciter not being fixed. To further secure the exciter 300, an exciter mount 240 is machined. The exciter mount 240 is provided with a first fixing region 242 fixed to the exciter mount ring 220, a second fixing region 243 for fixing to the exciter 300, and a second through hole 241 adapted to communicate with the exciter mount groove 222, the second through hole 241 being further adapted to be inserted into the exciter 300. The inclination angle of the second through hole 241 should be identical to that of the exciter mounting groove 222.

The first fixing region 242 is a through hole penetrating the upper and lower surfaces of the exciter mount 240, and the through hole of the first fixing region 242 corresponds to the screw hole 223. The second fixing region 243 is an optical hole penetrating the upper surface of the actuator mount 240 and the second through hole 241. Corresponding exciter 300 fixing threaded holes are provided at corresponding positions of the exciter 300 for testing. The exciter 300 is fixedly connected to the holder by screws.

The parameters associated with the exciter mount 240 are consistent with those on the exciter mount ring 220, ensuring fit. Specifically, the mounting surface 244 of the exciter mount 240 is a curved surface conforming to the curvature of the outer surface of the exciter mount ring 220, so that the exciter mount 240 can be secured in close contact with the exciter mount ring 220. The outlet of the second through hole 241 close to the axis of the rotor casing 210 is rounded, so that the fluid is not influenced by the structural shape as much as possible, and the direction and the oscillating structure of the outlet airflow are not changed.

The specific method of use of the multivariate test structure of the invention is as follows: the compressor experiment table rotor is driven by a motor, so that the control of the rotating speed is stable. In the experimental process, throttling is realized by axially moving the outlet conical valve, so that the working conditions of the gas compressor under different mass flow rates are obtained.

The actuator 300 employs a self-exciting oscillating jet actuator. The self-excited oscillating jet actuator has a variety of configurations, two of which are both pulsed, as shown in fig. 9 of the present invention. The velocity response diagram of the outlet of this form of self-excited oscillator at an inlet pressure of 1.0bar gauge and the working medium air is shown in figure 10. The above actuators are merely illustrative and other configurations of pulsed actuators or swept actuators (fig. 11) are equally suitable for testing using the multivariable test structure of the present invention. The actuators were mounted to the multivariable test structure of the present invention using an array of fluid actuators capable of generating self-exciting/self-sustaining oscillating jets and under external pressure, the operating frequency and amplitude at the jet outlet on the surface of the flow channel in the engine were adjusted by controlling the actuator inlet pressure through a manual regulating valve or solenoid valve.

In the experimental procedure, a non-fluidic experiment was first performed, in which all the actuators were closed and the characteristic line obtained at this time was used as a reference. Furthermore, the optimal stability-expanded pipeline length is found on the premise of ensuring the decoupling of the jet frequency and the pressure of the oscillator by adjusting the length of the pipeline for controlling the frequency of the exciter.

After the length of the exciter pipeline is determined, research on the influence of different space parameters on the stability margin of the compressor is carried out. In the experiment, 4 positions of the exciter are arranged in the axial direction, namely-0.4 c, -0.2c, 0c and 0.2c, wherein c is the chord length of the tip of the rotor, and the specific value is 119 mm. The axial position is referenced to the leading edge of the rotor blade tip, with positive values representing downstream and negative values representing upstream. In order to ensure that the exciters are uniformly distributed in the circumferential direction and are combined with the circumference of the experimental compressor rotor casing, the maximum number of the exciters is selected to be 30, so that the number of the exciters which can be uniformly distributed and can be opened in the experiment is respectively 5, 10, 15 and 30. In summary, a total of 16 experiments explored the effect of spatial position on actuator stability extension. In the experimental process, each group of experiments is subjected to three times of repeated experiments, so that errors are reduced, and accidental performance is avoided.

In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.

It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of description and are not intended to limit the scope of the invention. Other variations or modifications will occur to those skilled in the art based on the foregoing disclosure and are within the scope of the invention.

Claims

1. The utility model provides a compressor test structure, includes rotor machine casket, exciter collar and fixed part, its characterized in that:

the rotor casing is fixedly connected with the air inlet cone and the stator casing respectively, and a plurality of first through holes are formed in the rotor casing;

the exciter mounting ring is provided with a plurality of exciter mounting grooves which correspond to the first through holes and are arranged at an angle, and the mounting grooves are arranged in a penetrating manner; the exciter mounting ring is coaxially connected with the rotor casing, and the rotor casing is fixedly connected with the exciter mounting ring through the fixing part; the exciter mounting groove is adapted to be fixedly connected with an exciter and/or a baffle.

2. A compressor test structure as claimed in claim 1, wherein: the exciter mounting seat is provided with a first fixing area fixed with the exciter mounting ring, a second fixing area used for fixing with an exciter, and a second through hole suitable for being communicated with the exciter mounting groove, and the second through hole is also suitable for being inserted into the exciter.

3. A compressor test structure as claimed in claim 2, wherein: the first through hole and the exciter mounting groove have the same inclination angle, and the inclination angle and the axis of the rotor case form an included angle of not more than 30 degrees.

4. A compressor test structure as claimed in claim 3, wherein: the included angle is 25 degrees.

5. A compressor test structure as claimed in claim 2, wherein: the width of the exciter mounting groove is consistent with the thickness of the outlet part of the exciter.

6. A compressor test structure as claimed in claim 2, wherein: threaded holes are formed in two sides of the exciter mounting groove, the first fixing area is a through hole penetrating through the upper surface and the lower surface of the exciter mounting seat, and the through hole of the first fixing area corresponds to the threaded hole.

7. A compressor test structure as claimed in claim 2, wherein: and a round angle is arranged at an outlet of the second through hole, which is close to the axis of the rotor casing.

8. A compressor test structure as claimed in any one of claims 1 to 7, wherein: and the exciter mounting ring is also provided with a mounting hole for mounting a pressure pulsation sensor.

9. A compressor test structure as claimed in any one of claims 1 to 7, wherein: the circumference of rotor machine casket equally divides the aperture of a plurality of millimeters levels of processing, the aperture is used for installing the sensor of measuring rotor apex disturbance.

10. A compressor test structure as claimed in any one of claims 1 to 7, wherein: the fixing part comprises a plurality of positioning rings, the first through hole is a rectangular through hole, the long edge of the first through hole is parallel to the axis of the rotor case, the positioning rings are used for adjusting the position of the exciter mounting ring, and the exciter mounting groove is arranged in the corresponding range of the first through hole.

11. A compressor test structure as claimed in claim 10, wherein: the nozzle aerodynamic range of the exciter is-0.4 c to 0.2c, wherein c is the rotor blade tip chord length.

12. A compressor test structure as claimed in claim 11, wherein: the nozzle of the exciter is respectively positioned at the positions of-0.4 c, -0.2c, 0c and 0.2c away from the front edge of the rotor, wherein c is 118mm-120 mm.