Surge early warning system, surge early warning method and engine

Abstract

The invention belongs to the technical field of gas compressors, and provides a surge early warning system, a surge early warning method and an engine, the surge early warning system comprises a gas compressor, a blanking cap, a probe, a processing module and an alarm module; wherein a plurality of peepholes are formed in the surface of the gas compressor, and the plurality of blanking caps are mounted in the corresponding peepholes; part of the blanking cap is connected with the probe, and one end, far away from the blanking cap, of the probe is connected with the processing module; and the alarm module is connected with the processing module. A traditional engine blanking cap is improved, so that part of the blanking cap can be directly connected with a probe, the blanking cap becomes a switching structure for installing the probe, and early warning signal detection can be completed through simple blanking cap modification for a shaped engine model; the first blanking cap can be installed on the surface of a circumferential casing of a stator blade of a multi-stage gas compressor, when the gas compressor works, the probe connected with the first blanking cap can monitor all stages of enhanced gas flow in the gas compressor in real time, and therefore data support is provided for surge early warning.

Description

Technical Field

[0001] The invention belongs to the technical field of compressors, and in particular relates to a surge warning system, a surge warning method and an engine. Background Art

[0002] The design orientation of modern turbomachinery is developing towards high load and high efficiency. Higher single-stage pressure ratio and efficiency, as well as achieving higher load on fewer stages, have become key technologies in compressor / fan design. However, the higher the stage load of the compressor, the more stringent the requirements for its stable working conditions. The stable working range of the compressor is determined by its surge margin, that is, the possible flow rate and pressure ratio variation range between the compressor's operating point and the surge boundary point. If the compressor's surge margin is too small, once rotating stall or surge occurs, the engine performance will deteriorate sharply at the least, and the engine will shut down or the entire engine will be destroyed due to blade breakage. Therefore, widening the stable working range of the compressor and delaying the gas flow loss have become one of the key technologies in designing high-load compressors. The traditional surge control method belongs to passive control technology, the core of which is to ensure that there is enough margin between the compressor's operating point and the surge boundary, so that the compressor can work far away from the surge boundary point. However, the surge margin is often affected by factors such as flight conditions, engine operating conditions, and inlet flow field distortion, making it difficult to accurately determine, which seriously reduces the performance of the compressor. With the increase of compressor load, the contradiction between performance and surge margin becomes more prominent, and the idea of ​​active surge control is born in this situation.

[0003] The existing surge control of aircraft engines is a passive control after surge occurs. It is based on the monitoring of the compressor outlet pressure signal. This monitoring can only determine whether surge occurs, but cannot give early warning of surge. A large surge margin (the "distance" from the design point to the surge boundary) needs to be reserved during design. This control cannot avoid the occurrence of surge, and therefore cannot avoid the hazards caused by surge (such as engine failure, aircraft crash, etc.).

[0004] In addition, the best location to obtain the surge warning signal is the tip of the compressor rotor. However, in most compressors, the layout of the dynamic pressure probe faces many challenges. For example, if the probe is directly placed on the inner casing near the tip of the compressor rotor, it will be limited by the size of the probe, making this method unfeasible. At the same time, the dense and complex piping on the outside of the aircraft engine also makes it extremely difficult to arrange the surge warning signal monitoring probe. In addition, for models that have been finalized, irreversible drilling on the compressor casing is generally not allowed because it does not meet airworthiness requirements and the re-verification and certification process is very cumbersome. Summary of the invention

[0005] In order to solve at least one problem in the background technology, the present invention provides a surge warning system, a surge warning method and an engine.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A surge warning system comprises a compressor, a plugging cover, a probe, a processing module and an alarm module;

[0008] A plurality of peep holes are provided on the surface of the compressor;

[0009] A plurality of the blocking covers are installed in the corresponding peepholes;

[0010] A portion of the plugging cover is connected to the probe;

[0011] One end of the probe away from the plugging cover is connected to the processing module;

[0012] The alarm module is connected to the processing module.

[0013] Preferably, the compressor comprises a rotor and a casing;

[0014] The rotor surface is provided with a first rotor blade, a second rotor blade and a third rotor blade in sequence along the axial direction;

[0015] The inner surface of the casing is provided with a first stator blade, a second stator blade and a third stator blade in sequence along the axial direction;

[0016] The first stator blade is located between the first rotor blade and the second rotor blade, the second stator blade is located between the second rotor blade and the third rotor blade, and the third rotor blade is located between the second stator blade and the third stator blade.

[0017] Preferably, the casing is provided with the peep holes at positions corresponding to the first stator blade, the second stator blade and the third stator blade respectively.

[0018] Preferably, the casing circumferential surface corresponding to the first stator blade, the casing circumferential surface corresponding to the second stator blade and the casing circumferential surface corresponding to the third stator blade are each provided with at least two peep holes, and probes are installed on the plugging covers corresponding to at least two peep holes on each circumferential surface.

[0019] Preferably, the casing is a double-layer structure, and the double-layer structure includes an outer casing and an inner casing, and the outer casing is located outside the inner casing and is fixedly connected to the inner casing.

[0020] Preferably, the plugging cover comprises a first plugging cover and a second plugging cover;

[0021] The first blocking cover is a rotating body structure with a "T"-shaped cross section, and a threaded hole and a through hole connected in sequence are opened along the axial direction of the rotating body structure, and the aperture of the threaded hole is larger than the aperture of the through hole;

[0022] The threaded hole is used to connect the probe, and the through hole is connected to the inside of the casing;

[0023] The second blocking cover is a rotating body structure with a "T"-shaped cross section.

[0024] Preferably, a plurality of first fixing holes are provided on the step surface of the first blocking cover, and the first fixing holes are used to assemble screws connected to the casing;

[0025] A plurality of second fixing holes are provided on the step surface of the second blocking cover, and the second fixing holes are used for assembling screws connected to the casing.

[0026] Preferably, the model of the probe is XTEH-7L-190SM.

[0027] A surge warning method, applied to the above-mentioned surge warning system, comprises the following steps:

[0028] Install the probe on the plugging cap at the target location;

[0029] Monitor the internal pressure of the press through a probe and transmit the pressure signal to the processing module;

[0030] The processing module analyzes the pressure signal to determine whether the compressor has reached the surge warning range;

[0031] When the processing module determines that the compressor reaches the warning range of surge, a warning signal is sent out through the alarm module.

[0032] An engine is integrated with the above-mentioned surge warning system.

[0033] Beneficial effects of the present invention:

[0034] 1. The present invention improves the traditional engine plug cover so that part of the plug cover can be directly connected to the probe, making the plug cover a transfer structure for installing the probe. For the finalized engine model, the warning signal detection can be completed by simply modifying the plug cover, thereby providing technical support for the monitoring and early warning of surge warning signals;

[0035] 2. The first plugging cover of the present invention can be installed on the circumferential casing surface of the stator blades of a multi-stage compressor. When the compressor is working, the probe connected to the first plugging cover can monitor the enhanced airflow at each level inside the compressor, thereby providing data support for surge warning.

[0036] Other features and advantages of the present invention will be described in the following description, and partly become obvious from the description, or be understood by implementing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0038] Figure 1 The structure diagram of the surge warning system of the present invention is shown;

[0039] Figure 2 A schematic structural diagram of a compressor of the present invention is shown;

[0040] Figure 3 A schematic diagram showing the cooperation between the first blocking cover and the casing of the present invention is shown;

[0041] Figure 4 A schematic diagram showing the cooperation between the second plugging cover and the casing of the present invention is shown;

[0042] Figure 5 A schematic diagram of the structure of the probe of the present invention is shown;

[0043] Figure 6 A flow chart of the surge warning method of the present invention is shown.

[0044] In the figure: 1. rotor; 101. first rotor blade; 102. second rotor blade; 103. third rotor blade; 2. casing; 201. first stator blade; 202. second stator blade; 203. third stator blade; 204. peephole; 3. first plugging cover; 301. threaded hole; 302. through hole; 303. first fixing hole; 4. second plugging cover; 401. second fixing hole; 5. probe; 6. processing module; 7. alarm module; 8. electrical signal connector; 9. compensation module; 10. probe signal line; 11. support rod; 12. threaded connector. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0046] like Figure 1 As shown, it is a schematic diagram of the structure of the surge warning system, which includes a compressor, a plugging cover, a probe 5, a processing module 6 and an alarm module 7.

[0047] Combination Figure 2 It can be seen that the compressor includes a rotor 1 and a casing 2, and the first rotor blade 101, the second rotor blade 102 and the third rotor are sequentially installed on the surface of the rotor 1 along the axial direction. The first stator blade 201, the second stator blade 202 and the third stator blade 203 are sequentially installed on the inner surface of the casing 2 along the axial direction. At the same time, the first stator blade 201 is located between the first rotor blade 101 and the second rotor blade 102, the second stator blade 202 is located between the second rotor blade 102 and the third rotor blade 103, and the third rotor blade 103 is located between the second stator blade 202 and the third stator blade 203. In addition, the casing 2 is provided with peepholes 204 at the surface positions corresponding to the first stator, the second stator and the third stator, respectively.

[0048] It should be noted that the compressor mainly realizes "stage-by-stage" supercharging through the rotor 1 and the stator. The so-called "stage" consists of a row of rotor blades (rotational supercharging) and a row of stator blades (mainly for guiding flow). For example, the first rotor blade 101 and the first stator blade 201 form the first stage; the second rotor blade 102 and the second stator blade 202 form the second stage; the third rotor blade 103 and the third stator blade 203 form the third stage. Therefore Figure 1 The structure is a three-stage compressor. Of course, in actual application it is not limited to a three-stage compressor. The above system is applicable to various types of compressors.

[0049] As a preferred solution, the casing 2 is a double-layer structure, which includes an outer casing and an inner casing, wherein the outer casing is located outside the inner casing and is fixedly connected to the inner casing. The peephole 204 penetrates the double-layer structure so as to communicate with the inside of the casing 2.

[0050] Further, for the above three-stage compressor, each row of stator blades ( Figure 1At least two peep holes 204 are provided on the circumferential surface of the casing 2 corresponding to the first liquid inlet blade, the second stator blade 202 and the third stator blade 203, and the peep holes 204 are evenly distributed along the circumferential direction. In addition, at least two plugging covers for installing the connection probe 5 are provided in the peep holes 204 corresponding to each row of stator blades.

[0051] It should be noted that in Figure 1 In the structure, the circumference of the first stator blade 201, the second stator blade 202 and the third stator blade 203 corresponds to at least two (preferably four) peepholes 204, and each peephole 204 corresponding to the circumferential surface has at least two plugging covers for installing the connecting probe 5.

[0052] like Figure 3 and Figure 4 As shown, the plugging cover includes a first plugging cover 3 and a second plugging cover 4. The first plugging cover 3 in the figure is a rotating body structure with a "T"-shaped cross section, and a threaded hole 301 and a through hole 302 are opened in sequence along the axial direction of the rotating body structure. The aperture of the threaded hole 301 is larger than the aperture of the through hole 302. The threaded hole 301 is used to connect the probe 5, and the through hole 302 is connected to the inside of the casing 2. In addition, a plurality of first fixing holes 303 are opened on the step surface of the first plugging cover 3, and the first fixing holes 303 are used to assemble screws connected to the casing 2. Figure 4 The second blocking cover 4 is a rotating body structure with a cross section of "T". A plurality of second fixing holes 401 are provided on the step surface of the second blocking cover 4, and the second fixing holes 401 are used to assemble screws connected to the casing 2.

[0053] It should be noted that the peephole 204 is sealed by a plugging cover to prevent the compressor pressurized gas from leaking through the peephole 204. The second plugging cover 4 is a conventional peephole 204 plugging cover, which is mainly used for borescope inspection (similar to the endoscope inspection used in physical examination). The first plugging cover 3 is a plugging cover modified based on the second plugging cover 4. The first plugging cover 3 can be used for borescope, and can also be installed in the threaded hole 301 to monitor the dynamic pressure. The probe 5 can be used to monitor the surge warning signal. In addition, the plugging cover can be fixed to the peephole 204 by screws (for example, the first fixing hole 303 of the first plugging cover 3 is matched with a screw, and then connected to the surface of the casing 2, and then the first plugging cover 3 is fixed to the casing 2), and the two are sealed by a sealing gasket (not drawn in the schematic diagram) or a rubber ring (not drawn in the schematic diagram) to prevent the leakage of pressurized gas. In addition, there is a through hole 302 below the threaded hole 301 that is connected to the inside of the compressor, so that the probe 5 can sense the pressure change of the pressurized airflow inside the compressor, thereby realizing surge warning.

[0054] Furthermore, one end of the probe 5 away from the blocking cover is connected to the processing module 6 , and the alarm module 7 is connected to the processing module 6 .

[0055] It should be noted that the probe 5 can collect the pressure signal inside the casing 2. The processing module 6 analyzes the received pressure signal to determine whether the compressor will surge. If surge is about to occur, an alarm signal can be issued through the alarm module 7.

[0056] Furthermore, the model of the probe 5 is XTEH-7L-190SM. The probe 5 of the XTEH-7L-190SM includes an electrical signal connector 8, a compensation module 9, a probe signal line 10, a support rod 11 and a threaded connector 12, wherein one end of the electrical signal connector 8 is connected to the processing module 6, and the other end is connected to the compensation module 9 through a wire, the compensation module 9 is connected to the support rod 11 through the probe signal line 10, the probe signal line 10 passes through the support rod 11 and is connected to the threaded connector 12, and the threaded connector 12 cooperates with the threaded hole 301.

[0057] like Figure 5 As shown, the thread design of the threaded hole 301 needs to be determined according to the thread specifications of the selected probe 5. The selection of the specifications of the probe 5 is determined by the maximum pressure and maximum temperature of the pressurized airflow at the corresponding position of the threaded hole 301, so as to ensure that the probe 5 is not damaged by high temperature or high pressure. Figure 5 At this time, the thread design of the threaded hole 301 is M5.0×0.8, and the thread depth should be greater than 11.1 mm. The diameter of the through hole 302 is about 0.5-5 mm. The selection of the diameter of the through hole 302 should ensure that the cavity at this position is as small as possible.

[0058] like Figure 6 As shown, a compressor surge warning method is applied to the above compressor surge warning system, comprising the following steps:

[0059] S1: Install the probe 5 on the plugging cover at the target position;

[0060] S2: monitor the internal pressure of the press through the probe 5 and transmit the pressure signal to the processing module 6;

[0061] S3: Analyze the pressure signal through the processing module 6 to determine whether the compressor has reached the surge warning range (surge is about to occur);

[0062] S4: When the processing module 6 determines that the compressor reaches the surge warning range, a warning signal is issued through the alarm module 7.

[0063] It should be noted that, in an optional embodiment, the three-stage compressor is composed of three stages, and a probe 5 is installed on the plug cover at each stage of the stator blade. The probe 5 can accurately capture the changes in the internal pressure of the compressor. Then, when the compressor is running, the probe 5 starts to work, by monitoring the pressurized airflow inside the casing 2 corresponding to each stage of the stator blade of the compressor, and transmitting the pressure signal to the processing module 6 in real time. The processing module 6 is a high-performance data processing unit that can quickly and accurately analyze the received pressure signal. Next, the processing module 6 analyzes the received pressure signal and determines whether the compressor has reached the surge warning range by comparing the historical data with the preset surge warning threshold. If the change trend of the internal pressure of the compressor meets the characteristics of surge, and the pressure value is close to or exceeds the warning threshold, the processing module 6 will determine that the compressor is about to surge. In this embodiment, the warning threshold can be set for different stages of the three-stage compressor to more accurately determine the occurrence of surge. Finally, when the processing module 6 determines that the compressor has reached the surge warning range, it will immediately send a warning signal through the alarm module 7. The alarm module 7 can be a sound alarm, a light alarm or an alarm device connected to the central control system to ensure that the operator can promptly discover and take measures to prevent the occurrence of surge. In addition, in this embodiment, the operating parameters of the compressor can be adjusted according to the specific operating conditions of the three-stage compressor and the surge warning results, such as changing the speed, adjusting the inlet guide vane angle, etc., to further prevent the occurrence of surge and improve the operating stability and safety of the compressor. Through the surge warning method of this embodiment, the operating status of the three-stage compressor can be monitored in real time, the signs of surge can be discovered in time, and effective measures can be taken to avoid damage to the compressor caused by surge, thereby improving the operating reliability and safety of the compressor.

[0064] It should be further explained that the above method can monitor the early warning signal before the aircraft engine surge occurs (similar to the active emergency brake system in the automotive field, which can issue a warning before a rear-end collision occurs), ensure that the control system intervenes in advance to prevent the surge from occurring (similar to preventing the rear-end collision in the automotive field) or even if the surge occurs, the harm of the surge can be reduced (similar to reducing the harm of the rear-end collision even if a rear-end collision occurs in the automotive field), and ensure the safe operation of the aircraft engine. The surge warning signal monitoring mainly obtains the required warning signal through the modification of the aircraft engine peephole 204.

[0065] An engine is integrated with the above compressor surge warning system.

[0066] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein; and these modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A surge warning system, characterized in that: It comprises a compressor, a plugging cover, a probe (5), a processing module (6) and an alarm module (7); A plurality of peep holes (204) are provided on the surface of the compressor; A plurality of the blocking covers are installed in the corresponding peep holes (204); A portion of the plugging cover is connected to the probe (5); One end of the probe (5) away from the blocking cover is connected to the processing module (6); The alarm module (7) is connected to the processing module (6).

2. A surge warning system according to claim 1, characterized in that: The compressor comprises a rotor (1) and a casing (2); The surface of the rotor (1) is provided with a first rotor blade (101), a second rotor blade (102) and a third rotor blade (103) in sequence along the axial direction; The inner surface of the casing (2) is provided with a first stator blade (201), a second stator blade (202) and a third stator blade (203) in sequence along the axial direction; The first stator blade (201) is located between the first rotor blade (101) and the second rotor blade (102), the second stator blade (202) is located between the second rotor blade (102) and the third rotor blade (103), and the third rotor blade (103) is located between the second stator blade (202) and the third stator blade (203).

3. A surge warning system according to claim 2, characterized in that: The casing (2) is provided with the peep holes (204) at positions corresponding to the first stator blade (201), the second stator blade (202) and the third stator blade (203).

4. A surge warning system according to claim 2, characterized in that: The circumferential surface of the casing (2) corresponding to the first stator blade (201), the circumferential surface of the casing (2) corresponding to the second stator blade (202), and the circumferential surface of the casing (2) corresponding to the third stator blade (203) are all provided with at least two peep holes (204), and the plugging covers corresponding to at least two peep holes (204) on each circumferential surface are installed with probes (5).

5. A surge warning system according to claim 2, characterized in that: The casing (2) is a double-layer structure, comprising an outer casing and an inner casing, wherein the outer casing is located outside the inner casing and is fixedly connected to the inner casing.

6. A surge warning system according to any one of claims 1 to 5, characterized in that: The blocking cover comprises a first blocking cover (3) and a second blocking cover (4); The first blocking cover (3) is a rotating body structure with a "T"-shaped cross section, and a threaded hole (301) and a through hole (302) are provided in sequence along the axial direction of the rotating body structure, and the diameter of the threaded hole (301) is larger than the diameter of the through hole (302); The threaded hole (301) is used to connect the probe (5), and the through hole (302) is connected to the inside of the casing (2); The second blocking cover (4) is a rotating body structure with a T-shaped cross section.

7. A surge warning system according to claim 6, characterized in that: A plurality of first fixing holes (303) are provided on the step surface of the first blocking cover (3), and the first fixing holes (303) are used to assemble screws connected to the casing (2); A plurality of second fixing holes (401) are provided on the step surface of the second blocking cover (4), and the second fixing holes (401) are used for assembling screws connected to the casing (2).

8. A surge warning system according to claim 1, characterized in that: The model of the probe (5) is XTEH-7L-190SM.

9. A surge warning method, applied to a surge warning system according to any one of claims 1 to 8, characterized in that: The following steps are involved: Installing the probe (5) on the plugging cover at the target position; The internal pressure of the press is monitored by a probe (5) and the pressure signal is transmitted to a processing module (6); Analyzing the pressure signal through a processing module (6) to determine whether the compressor has reached a surge warning range; When the processing module (6) determines that the compressor has reached the warning range of surge, a warning signal is sent out through the alarm module (7).

10. An engine, characterized in that: A surge warning system according to any one of claims 1 to 8 is integrated.

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