Gas turbine primary moving blade cooling hole flow test system

Abstract

The utility model relates to a gas turbine primary moving blade cooling hole flow test system, which comprises a flow test subsystem and a connecting piece, and the flow test subsystem is provided with a connecting interface; the connecting piece is provided with a circulation cavity, an air inlet and an air outlet which are communicated with the circulation cavity are formed in the two ends of the connecting piece, the air inlet is matched with the connecting port in shape and communicated with the connecting port, and the air outlet is matched with the blade tenon teeth in shape and communicated with the cooling holes in the blade tenon teeth. The connecting piece is provided with a movable blade front gas pressure sensor which is used for measuring the pressure in the circulation cavity; and the flow test subsystem is matched with the moving blade front gas pressure sensor to test the flow of the moving blade cooling hole. According to the testing system, the flow testing subsystem, the connecting piece and the moving blade front gas pressure sensor are used in cooperation, the problem that the measurement of the first-stage moving blade flow of the gas turbine is long in consumed time is solved, and the testing system has the advantages of being easy and convenient to operate and accurate in measurement.

Description

Technical Field

[0001] The utility model relates to the technical field of gas turbine blade cooling hole flow measurement, in particular to a gas turbine first-stage moving blade cooling hole flow measurement system. Background Art

[0002] Gas turbines are widely used in multiple industries such as power generation, aviation, oil and natural gas. During operation, the first-stage moving blades of the gas turbine turbine directly bear the erosion of high-temperature gas. Among them, the gas working temperature of the gas turbine is about 1200°C. Such a high temperature will cause the blade material to fail rapidly. Therefore, cooling channels are designed inside the first-stage moving blades of the turbine to reduce the blade temperature, reduce thermal stress and thermal fatigue, thereby extending the service life of the blades. Processing problems or blockages in the cooling holes will cause local overheating of the blades, which may lead to premature failure of the blades. Ensuring the structural integrity and smoothness of the cooling holes is crucial for the reliability and stability of the gas turbine operation, and can reduce downtime caused by blade failures.

[0003] Measuring the flow rate of the first-stage moving blades of the gas turbine turbine requires sending the blades to a professional testing institution, which is time-consuming and cumbersome. On the one hand, to solve the "bottleneck" problem of domestic production of gas turbine turbine blades, many domestic units are currently carrying out relevant work around this problem. The flow rate of the blade cooling channel, as an important indicator for judging the qualification of blade design and manufacturing, is an essential test item during the domestic production process; on the other hand, the flow rate test of the blade can also reflect the state of the internal cooling channel of the blade, and is also an important test item during the gas turbine maintenance process. Therefore, a convenient and fast blade flow cooling hole detection system is crucial. Summary of the Utility Model

[0004] The utility model provides a gas turbine first-stage moving blade cooling hole flow measurement system. By the combined use of a flow measurement subsystem, a connecting piece and a gas pressure sensor in front of the moving blade, the problem of long time-consuming for measuring the flow rate of the first-stage moving blades of the gas turbine is solved, and it has the characteristics of simple operation and accurate measurement.

[0005] To achieve the above object, the utility model adopts the following technical solutions:

[0006] A gas turbine first-stage moving blade cooling hole flow measurement system includes a flow measurement subsystem and a connecting piece. The flow measurement subsystem has a connection interface;

[0007] The connecting piece has a flow cavity. An air inlet and an air outlet communicating with the flow cavity are opened at both ends of the connecting piece. The shape of the air inlet is adapted to and communicates with the shape of the connection interface, and the shape of the air outlet is adapted to the last-stage tenon tooth of the blade tenon tooth and communicates with the cooling hole therein;

[0008] The above-mentioned connecting piece is provided with a gas pressure sensor before the moving blade to measure the pressure in the above-mentioned flow cavity;

[0009] The above-mentioned flow rate testing subsystem cooperates with the above-mentioned gas pressure sensor before the moving blade to test the flow rate of the moving blade cooling holes.

[0010] Preferably, the above-mentioned connecting piece includes a first connector, a first transition section, a connecting body, a second transition section and a second connector connected in sequence;

[0011] The above-mentioned air inlet is arranged on the above-mentioned first connector, and the above-mentioned air outlet is arranged on the above-mentioned second connector;

[0012] The inner diameter of the above-mentioned first transition section gradually increases along the air flow direction. The maximum inner diameter of the above-mentioned first transition section is the same as the inner diameter of the above-mentioned connecting body, and the minimum inner diameter is the same as the diameter of the above-mentioned air inlet;

[0013] The inner diameter of the above-mentioned second transition section gradually decreases along the air flow direction. The maximum inner diameter of the above-mentioned second transition section is the same as the inner diameter of the above-mentioned connecting body, and the minimum inner diameter is the same as the diameter of the above-mentioned air outlet.

[0014] Preferably, a flow stabilizing component for stabilizing the air flow is arranged in the cavity of the above-mentioned connecting body, and the above-mentioned flow stabilizing component is located at the end of the above-mentioned first transition section close to the above-mentioned connecting body.

[0015] Preferably, the above-mentioned flow stabilizing component includes a grille, and the above-mentioned grille has a certain length along the air flow direction.

[0016] Preferably, the length of the above-mentioned grille is 1 / 10 - 1 / 3 of the inner cavity length of the above-mentioned connecting body.

[0017] Preferably, the above-mentioned grille is composed of multiple metal thin sheets.

[0018] Preferably, the above-mentioned flow rate testing subsystem further includes a measurement medium gas source interface, a manual shut-off valve, a pre-filter for the pressure reducing valve, an electronically controlled pressure reducing valve, a pressure sensor for the pressure stabilizing tank, a temperature sensor for the pressure stabilizing tank, a pressure stabilizing gas tank, a Laval nozzle throttling element, a pressure sensor after the throttling element and a pre-filter; the above-mentioned measurement medium gas source interface, the pre-filter for the pressure reducing valve, the pressure stabilizing gas tank, the Laval nozzle throttling element, the pre-filter and the connection interface are connected in sequence. A manual shut-off valve is arranged between the above-mentioned measurement medium gas source interface and the pre-filter for the pressure reducing valve, an electronically controlled pressure reducing valve is arranged between the above-mentioned pre-filter for the pressure reducing valve and the pressure stabilizing gas tank, a pressure sensor for the pressure stabilizing tank and a temperature sensor for the pressure stabilizing tank are arranged on the above-mentioned pressure stabilizing gas tank, and a pressure sensor after the throttling element is arranged between the above-mentioned Laval nozzle throttling element and the pre-filter.

[0019] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0020] The connection interface in the flow rate test subsystem is connected to the cooling holes at the blade tenons of the first-stage moving blades through a connecting piece to supply gas to the blade cooling holes. Then, by the combined use of the flow rate test subsystem and the gas pressure sensor in front of the moving blade, the problem of measuring the flow rate of the first-stage moving blades of a gas turbine and the long time-consuming is solved, and it has the characteristics of simple operation and accurate measurement. Brief Description of the Drawings

[0021] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0022] Figure 1 It is the overall schematic diagram of the system in the embodiment of the present invention;

[0023] Figure 2 It is the cross-sectional schematic diagram of the connecting piece in the embodiment of the present invention;

[0024] Figure 3 It is the overall schematic diagram of the connecting piece in the embodiment of the present invention.

[0025] Description of the Reference Numerals:

[0026] 1. Flow rate test subsystem; 11. Measuring medium gas source interface; 12. Manual shut-off valve; 13. Filter before the pressure reducing valve; 14. Electric control pressure reducing valve; 15. Pressure sensor of the pressure stabilizing tank; 16. Temperature sensor of the pressure stabilizing tank; 17. Pressure stabilizing gas tank; 18. Laval nozzle throttling element; 19. Pressure sensor after the throttling element; 20. Filter; 201. Connection interface; 2. Connecting piece; 21. First connector; 22. First transition section; 23. Connection main body; 24. Second transition section; 25. Second connector; 26. Air inlet; 27. Air outlet; 28. Grid; 3. Gas pressure sensor in front of the moving blade. Specific Embodiments

[0027] The following will clearly and completely describe the technical solutions of the present invention with reference to the drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0028] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0029] In the description of the present utility model, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", "coupled" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0030] As Figures 1-3 shown, the embodiment of the present utility model provides a gas turbine first-stage moving blade cooling hole flow rate measurement system, which includes a flow rate measurement subsystem 1 and a connector 2. The flow rate measurement subsystem 1 is used for supplying gas and measuring the gas flow rate, which is a prior art (for details, see the gas turbine nozzle flow rate measurement system and measurement method based on the Laval nozzle principle with the patent number CN108731924B). It has a connection interface 201, and the connector 2 serves as an intermediate body connecting the flow rate measurement subsystem 1 and the first-stage moving blade. It has a flow cavity, and an air inlet 26 and an air outlet 27 communicating with the flow cavity are opened at both ends. In this embodiment, the shape of the air inlet 26 is adapted to and communicates with the shape of the connection interface 201, and the shape of the air outlet 27 is adapted to and communicates with the last-stage tenon tooth of the blade tenon tooth and the cooling hole therein. Thus, the connection interface 201 is indirectly communicated with the first-stage moving blade cooling hole through the connector 2 to supply gas to the cooling hole. In order to measure the gas pressure before the air enters the first-stage moving blade cooling hole, a gas pressure sensor 3 before the moving blade is provided on the connector 2 to measure the pressure in the flow cavity. Thus, the flow rate of the moving blade cooling hole is measured by the cooperation of the flow rate measurement subsystem 1 and the gas pressure sensor 3 before the moving blade. By the combined use of the flow rate measurement subsystem 1, the connector 2 and the gas pressure sensor 3 before the moving blade, the problem of measuring the flow rate of the first-stage moving blade of the gas turbine and the long time consumption is solved, and it has the characteristics of simple operation and accurate measurement.

[0031] Among them, in addition to the connection interface 201, the flow rate test subsystem 1 further includes a measuring medium gas source interface 11, a manual shut-off valve 12, a filter screen in front of the pressure reducing valve 13, an electronically controlled pressure reducing valve 14, a pressure sensor 15 for the pressure stabilizing tank, a temperature sensor 16 for the pressure stabilizing tank, a pressure stabilizing gas tank 17, a Laval nozzle throttling element 18, a pressure sensor 19 behind the throttling element, and a filter screen 20; the measuring medium gas source interface 11, the filter screen 13 in front of the pressure reducing valve, the pressure stabilizing gas tank 17, the Laval nozzle throttling element 18, the filter screen 20, and the connection interface 201 are connected in sequence. A manual shut-off valve 12 is arranged between the measuring medium gas source interface 11 and the filter screen 13 in front of the pressure reducing valve. A flexible connection is adopted between the measuring medium gas source interface 11 and the manual shut-off valve 12. An electronically controlled pressure reducing valve 14 is arranged between the filter screen 13 in front of the pressure reducing valve and the pressure stabilizing gas tank 17. A pressure sensor 15 for the pressure stabilizing tank and a temperature sensor 16 for the pressure stabilizing tank are arranged on the pressure stabilizing gas tank 17 for collecting the pressure value and temperature value inside the pressure stabilizing gas tank 17; the Laval nozzle throttling element 18 is in contact with the pressure stabilizing gas tank 17. The Laval nozzle throttling element 18 is a replaceable component with a detachable structure, and its profile is convergent-divergent. It can be replaced with a suitable component according to needs to correspond to different flow rates required by the moving blades. A flexible connection is adopted between the Laval nozzle throttling element 18 and the filter screen 20. A pressure sensor 19 behind the throttling element is arranged between the Laval nozzle throttling element 18 and the filter screen 20. The opening degree of the electronically controlled pressure reducing valve 14 is controlled by calculating in combination with the collected data of the pressure sensor 15 for the pressure stabilizing tank and the temperature sensor 16 for the pressure stabilizing tank to ensure that the pressure inside the pressure stabilizing gas tank 17 is always greater than the critical pressure of the Laval nozzle throttling element 18. The flow rate characteristics of the cooling holes of the tested first-stage moving blades can be calculated by the gas pressure sensor 3 in front of the moving blades in combination with the collected data of the pressure sensor 15 for the pressure stabilizing tank and the temperature sensor 16 for the pressure stabilizing tank.

[0032] The only difference between the flow rate test subsystem 1 in this embodiment and the original patent (a gas turbine nozzle flow rate test system based on the Laval nozzle principle) is that: in the original patent, the connection interface 201 is directly connected to the combustion chamber nozzle, so the pressure sensor in front of the combustion chamber nozzle at the nozzle inlet is arranged in front of the connection interface 201. In this embodiment, a connecting piece 2 is arranged to connect the connection interface 201 of the flow rate test subsystem 1 with the cooling holes of the first-stage moving blades. Therefore, the gas pressure sensor 3 in front of the moving blades is arranged on the connecting piece 2 to accurately measure the pressure of the gas before entering the cooling holes of the moving blades and accurately calculate the flow rate. And the methods of calculating the flow rate of the two systems are the same.

[0033] It should be noted that when installing the blade, after the blade tenon tooth is inserted into the air outlet 27, in order to avoid air leakage, white silica gel is used for further sealing. Air flows out from the air outlet 27 and enters the cooling holes at the bottom of the blade tenon tooth, and finally the gas flows out from the blade top, thus completing the circulation of air in the cooling holes.

[0034] Specifically, the connecting member 2 includes a first connector 21, a first transition section 22, a connecting body 23, a second transition section 24, and a second connector 25 that are connected in sequence. An air inlet 26 is opened on the first connector 21, and an air outlet 27 is opened on the second connector 25. To ensure stable gas flow, the inner diameter of the first transition section 22 gradually increases along the air flow direction. The maximum inner diameter of the first transition section 22 is the same as the inner diameter of the connecting body 23, and the minimum inner diameter is the same as the diameter of the air inlet 26. The inner diameter of the second transition section 24 gradually decreases along the air flow direction. The maximum inner diameter of the second transition section 24 is the same as the inner diameter of the connecting body 23, and the minimum inner diameter is the same as the diameter of the air outlet 27. Thus, the gas enters from the air inlet 26 and successively passes through the first connector 21, the first transition section 22, the connecting body 23, the second transition section 24, and the second connector 25, and enters the internal cooling holes of the blade tenon teeth through the air outlet 27. Specifically, a through hole communicating with the cavity is provided on the outer side wall of the connecting body 23, and the gas pressure sensor 3 in front of the moving blade is installed at the through hole.

[0035] Preferably, a flow stabilizing component is provided in the cavity of the connecting body 23, so that when the air passing through the flow stabilizing component flows in the flow cavity of the connecting member 2, the occurrence of turbulence is reduced, the uniformity of the air flow velocity is improved, and the air flows stably; preferably, the flow stabilizing component is located at the end of the first transition section 22 close to the connecting body 23.

[0036] Specifically, in this embodiment, the flow stabilizing component includes a grille 28. The grille 28 is provided in the cavity of the connecting body 23, and divides the cross-section of the cavity of the connecting body 23 into multiple flow channels. Thus, the air passes through the multiple flow channels, so that the air is divided into multiple strands, flows in layers, and has a directionality, avoiding the mixing of air up and down to a certain extent, and finally preventing the occurrence of turbulence, so that the air flows stably in the connecting member 2. Preferably, the grille 28 has a certain length along the air flow direction, that is, each flow channel in the grille 28 has a certain length, so that the air can flow along the flow channel for a certain distance and flow in layers, further reducing the probability of turbulence occurring in the connecting body 23.

[0037] Preferably, the length of the grille 28 is 1 / 10 - 1 / 3 of the inner cavity length of the connecting body 23 to ensure the distance of the stratified air flow.

[0038] Preferably, the grille 28 is composed of multiple metal thin sheets, which not only ensures the connection strength but also reduces the distance between the flow channels. Moreover, the shape of the grille 28 is the same as the shape of the cavity in the connecting body 23 to ensure that the edge of the grille 28 abuts against the inner wall of the cavity of the connecting body 23.

[0039] The above embodiments are only the preferred embodiments of the present utility model, and cannot be used to limit the scope of protection of the present utility model. Any non-substantive changes and substitutions made by those skilled in the art based on the present utility model fall within the scope of protection required by the present utility model.

Claims

1. A gas turbine turbine first stage moving blade cooling hole flow rate test system, characterized in that: It includes a flow test subsystem and a connector, wherein the flow test subsystem has a connection interface; The connecting piece has a circulation cavity, and an air inlet and an air outlet connected to the circulation cavity are provided at both ends of the connecting piece, the shape of the air inlet is adapted to and connected to the shape of the connection interface, and the shape of the air outlet is adapted to and connected to the last-stage tenon of the blade and connected to the cooling hole therein; The connecting piece is provided with a gas pressure sensor in front of the moving blade, so as to measure the pressure in the flow cavity; The flow rate test subsystem cooperates with the gas pressure sensor in front of the moving blade to test the flow rate of the cooling hole of the moving blade.

2. The moving blade cooling hole flow rate test system according to claim 1, characterized in that: The connecting piece comprises a first connecting head, a first transition section, a connecting body, a second transition section and a second connecting head which are connected in sequence; The air inlet is provided at the first connector, and the air outlet is provided at the second connector; The inner diameter of the first transition section gradually increases along the air flow direction, the maximum inner diameter of the first transition section is the same as the inner diameter of the connecting body, and the minimum inner diameter is the same as the diameter of the air inlet; The inner diameter of the second transition section gradually decreases along the air flow direction, the maximum inner diameter of the second transition section is the same as the inner diameter of the connecting body, and the minimum inner diameter is the same as the diameter of the air outlet.

3. The moving blade cooling hole flow rate test system according to claim 2, characterized in that: A flow stabilizing component for stabilizing the flow of air is disposed in the cavity of the connection body, and the flow stabilizing component is located in the first transition section close to the end of the connection body.

4. The moving blade cooling hole flow rate test system according to claim 3, characterized in that: The flow stabilizing component comprises a grille, and the grille has a certain length along the air flow direction.

5. The moving blade cooling hole flow rate test system according to claim 4, characterized in that: The length of the grid is 1 / 10-1 / 3 of the length of the inner cavity of the connecting body.

6. The moving blade cooling hole flow rate test system according to claim 4, characterized in that: The grid is composed of a plurality of metal sheets.

7. The moving blade cooling hole flow rate test system according to claim 1, characterized in that: The flow test subsystem also includes a measuring medium gas source interface, a manual shut-off valve, a front filter of a pressure reducing valve, an electrically controlled pressure reducing valve, a pressure regulating tank pressure sensor, a pressure regulating tank temperature sensor, a pressure regulating gas tank, a Laval nozzle throttling element, a pressure sensor after the throttling element, and a front filter; the measuring medium gas source interface, the front filter of the pressure reducing valve, the pressure regulating gas tank, the Laval nozzle throttling element, the front filter, and the connecting interface are connected in sequence, a manual shut-off valve is arranged between the measuring medium gas source interface and the front filter of the pressure reducing valve, an electrically controlled pressure reducing valve is arranged between the front filter of the pressure reducing valve and the pressure regulating gas tank, a pressure regulating tank pressure sensor and a pressure regulating tank temperature sensor are arranged on the pressure regulating gas tank, and a pressure sensor after the throttling element is arranged between the Laval nozzle throttling element and the front filter.

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