Turbine housing temperature difference cooling balancing device in gas turbine unit

Abstract

The utility model relates to the technical field of gas turbine generator sets, in particular to a turbine housing temperature difference cooling balance device in a gas turbine unit, which comprises two groups of cooling execution parts respectively mounted at the top of a cylinder body of a high-pressure cylinder and the top of a cylinder body of an intermediate-pressure cylinder, and the cooling execution parts are of shell plate structures matched with the outline of the peripheral wall of the cylinder body; a gap is reserved between the cooling execution part and the peripheral wall of the cylinder body, a cooling cavity is formed, the distance of the gap ranges from 95 mm to 105 mm, air inlet pipes are connected to the two side ends of the cooling execution part, an exhaust pipe is arranged in the middle of the cooling execution part, the two air inlet pipes are both connected to a cold air supply system, and the cold air supply system is electrically connected to a temperature control system of a turbine housing. And the two air inlet pipes are respectively provided with an electric control ball valve for automatically adjusting the air quantity. According to the turbine housing temperature difference cooling balancing device in the gas turbine unit, the temperature difference between the two cylinder bodies can be rapidly and accurately reduced, and the heat exchange effect and the temperature difference reducing effect are better in the non-manual control and operation mode.

Description

Technical Field

[0001] This application relates to the field of gas turbine generator set technology, and in particular to a gas turbine casing temperature difference cooling and balancing device in a gas turbine generator set. Background Technology

[0002] Taking the "two-to-one" mode as an example, the new gas turbine generator set does not have a cylinder cooling device designed for the turbine body. After the unit is put into operation, there is often a problem of large temperature difference between the upper and lower cylinders (i.e., high-pressure cylinder and intermediate-pressure cylinder). Excessive temperature difference between the upper and lower cylinders and the inner and outer walls may cause cylinder deformation, causing friction between the moving and stationary parts of the turbine, inducing turbine vibration, or even causing the main shaft to bend, which poses a significant safety hazard.

[0003] Currently, a relatively simple method on the market to eliminate cylinder temperature difference is to install a tube bundle on the upper part of the turbine cylinder, with small air holes evenly arranged on the tube bundle. The air outlet direction of the air holes is tangent to the circumferential direction of the cylinder wall, so that the air is evenly discharged and the cylinder is not locally heated. However, the amount of cooling air is manually controlled. This method is often greatly affected by environmental and human factors, and the heat exchange effect and the effect of reducing temperature difference are not ideal. Utility Model Content

[0004] This application provides a turbine casing temperature difference cooling and balancing device for gas turbine units to improve the following technical problems:

[0005] Currently, among the methods for eliminating cylinder block temperature differences on the market, the amount of cooling air is manually controlled. This method is often greatly affected by environmental and human factors, and the heat exchange effect and the effect of reducing temperature differences are not ideal.

[0006] This application provides a temperature difference cooling and balancing device for the turbine casing in a gas turbine unit, which adopts the following technical solution:

[0007] A turbine casing temperature difference cooling balancing device for a gas turbine unit includes two cooling actuators respectively installed on the top of the high-pressure cylinder and the top of the intermediate-pressure cylinder. The cooling actuator is a shell plate structure that fits the contour of the outer peripheral wall of the cylinder. A gap is reserved between the cooling actuator and the outer peripheral wall of the cylinder to form a cooling chamber. The distance of the gap is between 95-105mm. Air inlet pipes are connected to both ends of the cooling actuator, and an exhaust pipe is provided in the middle of the cooling actuator. Both air inlet pipes are connected to a cold air supply system. The cold air supply system is electrically connected to the temperature control system of the turbine casing. Each of the two air inlet pipes is equipped with an electrically controlled ball valve for automatically adjusting the gas volume.

[0008] In one feasible technical solution of this application, the cooling actuator includes a cooling shell plate and a bolt connection group, wherein the cooling shell plate is fixed to the cylinder body by multiple sets of the bolt connection group and forms the gap.

[0009] In one feasible technical solution of this application, the nut portion of the bolt connection group is welded and fixed to the outer peripheral wall of the cylinder, and the bolt portion of the bolt connection group is threadedly assembled to the cooling shell plate.

[0010] In one feasible technical solution of this application, the cooling shell plate is a stainless steel plate with an arc structure, and the two sides of the cooling shell plate are provided with planar steps for installing the air intake pipe.

[0011] In one feasible technical solution of this application, the lower surface of the cooling shell plate is provided with a heat-resistant coating.

[0012] In one feasible technical solution of this application, a heat insulation layer is provided on the upper surface of the cooling shell plate, the outer peripheral wall of the air intake pipe, and the outer peripheral wall of the exhaust pipe.

[0013] In one feasible technical solution of this application, the air supply system includes a heat exchanger with compressed air as the cooling medium. The heat exchanger has an inlet pipe and an outlet pipe at its two ends, and both inlet pipes are connected to the outlet pipe. A bypass pipe is also provided between the inlet pipe and the outlet pipe. The outlet pipe is also provided with an on / off ball valve, a regulating ball valve, a booster pump and a temperature sensor in sequence.

[0014] In one feasible technical solution of this application, the temperature sensor is located between the two electrically controlled ball valves, and the booster pump is located at the front end of the two air intake pipes.

[0015] In one feasible technical solution of this application, an inlet ball valve is further provided on the inlet pipe, an outlet ball valve is further provided on the outlet pipe, and a bypass ball valve is further provided on the bypass pipe.

[0016] In one feasible technical solution of this application, the outlet temperature of the heat exchanger is adjustable between 50-450℃, the outlet pressure of the heat exchanger is between 0.4-0.8 MPa, and the flow rate of the heat exchanger is between 3-6 m³ / h. 3 Between / min.

[0017] In summary, this application includes at least one of the following beneficial technical effects:

[0018] By linking the cooling air supply system and the turbine casing temperature control system, when the temperature difference between the high-pressure cylinder and the intermediate-pressure cylinder is too large, the cooling air supply system can be activated and two electrically controlled ball valves can be automatically opened to control the cooling air flow in the two intake pipes respectively, thereby quickly and accurately reducing the temperature difference between the two cylinders. This non-human control and operation mode can basically eliminate environmental and human factors, and the heat exchange effect and temperature difference reduction effect are better. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the principle of the turbine casing temperature difference cooling balance device in the gas turbine unit according to an embodiment of this application.

[0021] Figure 2 This is a schematic diagram of the cooling actuator and the insulation layer in the embodiments of this application.

[0022] Explanation of reference numerals in the attached figures:

[0023] 1. Cooling actuator; 11. Cooling shell plate; 111. Planar step; 12. Bolted connection assembly; 13. Heat-resistant coating;

[0024] 2. Air intake pipe;

[0025] 3. Exhaust pipe;

[0026] 4. Air conditioning supply system; 41. Heat exchanger; 42. Inlet pipe; 421. Inlet ball valve; 43. Outlet pipe; 431. Outlet ball valve; 44. Bypass pipe; 441. Bypass ball valve; 45. On / off ball valve; 46. Regulating ball valve; 47. Booster pump; 48. Temperature sensor;

[0027] 5. Electrically controlled ball valve;

[0028] 6. Insulation layer;

[0029] 100. Cooling chamber; Detailed Implementation

[0030] To make the technical problems, technical solutions, and beneficial effects to be solved by this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the scope of this application.

[0031] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0032] It should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0033] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0034] The following is in conjunction with the appendix Figure 1-2 This application will be described in further detail.

[0035] This application discloses a temperature difference cooling and balancing device for the turbine casing in a gas turbine unit. (Refer to...) Figure 1-2 The turbine casing temperature difference cooling balancing device in the gas turbine unit includes two cooling actuators 1 installed on the top of the high-pressure cylinder and the top of the intermediate-pressure cylinder respectively. The cooling actuator 1 is a shell plate structure that fits the contour of the outer peripheral wall of the cylinder. A gap is reserved between the cooling actuator 1 and the outer peripheral wall of the cylinder to form a cooling chamber 100. The gap distance is between 95-105mm. The two ends of the cooling actuator 1 are connected to the air inlet pipes 2, and the middle of the cooling actuator 1 is provided with the exhaust pipe 3. Both air inlet pipes 2 are connected to the cold air supply system 4. The cold air supply system 4 is electrically connected to the temperature control system of the turbine casing. The two air inlet pipes 2 are respectively provided with an electrically controlled ball valve 5 for automatically adjusting the gas volume.

[0036] In this embodiment, the cooling actuator 1 includes a cooling shell plate 11 and a bolt connection group 12. The cooling shell plate 11 is fixed to the cylinder body by multiple bolt connection groups 12 and forms a gap. The nut part of the bolt connection group 12 is welded and fixed to the outer peripheral wall of the cylinder body. The bolt part of the bolt connection group 12 is threaded onto the cooling shell plate 11. The cooling shell plate 11 is a stainless steel plate with an arc structure. The two sides of the cooling shell plate 11 are provided with planar steps 111 for installing the intake pipe 2. The lower surface of the cooling shell plate 11 is provided with a heat-resistant coating 13. The upper surface of the cooling shell plate 11, the outer peripheral wall of the intake pipe 2, and the outer peripheral wall of the exhaust pipe 3 are all provided with a heat insulation layer 6.

[0037] The cooling actuator 1 designed above has a robust structure and is easy to install. It has low manufacturing and maintenance costs, is more adaptable, and can better ensure that the cold air is evenly distributed on the outer peripheral wall of the cylinder, thereby achieving a better cooling effect.

[0038] In this embodiment, the air supply system 4 includes a heat exchanger 41 using compressed air as the cooling medium. An inlet pipe 42 and an outlet pipe 43 are respectively provided at both ends of the heat exchanger 41. Both inlet pipes 2 are connected to the outlet pipe 43. A bypass pipe 44 is also provided between the inlet pipe 42 and the outlet pipe 43. An on / off ball valve 45, a regulating ball valve 46, a booster pump 47, and a temperature sensor 48 are sequentially provided on the outlet pipe 43. The temperature sensor 48 is positioned... Between the two electrically controlled ball valves 5, a booster pump 47 is located at the front end of the two inlet pipes 2. An inlet ball valve 421 is also installed on the inlet pipe 42, an outlet ball valve 431 is also installed on the outlet pipe 43, and a bypass ball valve 441 is also installed on the bypass pipe 44. The outlet temperature of the heat exchanger 41 is adjustable between 50-450℃, the outlet pressure of the heat exchanger 41 is between 0.4-0.8 MPa, and the flow rate of the heat exchanger 41 is between 3-6 m³ / h. 3 Between / min.

[0039] The above-designed air supply system 4 has a simple structure, stable operation, and convenient operation. It can also provide a large amount of cold air in a long-term stable and continuous manner to ensure a better cylinder temperature difference elimination effect.

[0040] In this embodiment, the bypass ball valve 441 is normally closed, while all other ball valves are normally open.

[0041] The beneficial technical effects of the turbine casing temperature difference cooling balancing device in the gas turbine unit of this application embodiment are roughly as follows:

[0042] By linking the cold air supply system 4 with the temperature control system of the turbine casing, when the temperature difference between the cylinder body of the high-pressure cylinder and the cylinder body of the intermediate-pressure cylinder is too large, the cold air supply system 4 can be started and the two electrically controlled ball valves 5 can be automatically opened to control the flow of cold air in the two intake pipes 2 respectively, thereby quickly and accurately reducing the temperature difference between the two cylinder bodies. This non-human control and operation mode can basically eliminate environmental and human factors, and the heat exchange effect and temperature difference reduction effect are better.

[0043] It has a wide range of applications and can be used for steam turbines that are not equipped with cylinder cooling. The installation and modification methods are simple, no special materials are required, the connection between the equipment and the cylinder is stable and does not damage the cylinder, the labor and material costs are low, the maintenance is simple, the capital investment is small, the heat exchange effect is good, compressed air is used as the heat exchange medium, and the device is reasonably arranged so that the air can circulate at high speed to remove heat. It can also respond quickly and adjust stably according to the start-up and shutdown requirements.

[0044] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A temperature difference cooling equalizer for a steam turbine casing in a gas turbine unit, characterized in that It includes two sets of cooling actuators (1) installed on the top of the cylinder body of the high-pressure cylinder and the top of the cylinder body of the intermediate-pressure cylinder, respectively. The cooling actuator (1) is a shell plate structure that fits the outline of the outer peripheral wall of the cylinder body. A gap is reserved between the cooling actuator (1) and the outer peripheral wall of the cylinder body to form a cooling chamber (100). The distance of the gap is between 95-105mm. The two ends of the cooling actuator (1) are connected to the air inlet pipe (2). An exhaust pipe (3) is provided in the middle of the cooling actuator (1). Both air inlet pipes (2) are connected to the cold air supply system (4). The cold air supply system (4) is electrically connected to the temperature control system of the turbine casing. Each of the two air inlet pipes (2) is provided with an electrically controlled ball valve (5) for automatically adjusting the gas volume.

2. The temperature difference cooling equalizer for a steam turbine casing of a gas turbine unit according to claim 1, characterized in that The cooling actuator (1) includes a cooling shell plate (11) and a bolt connection group (12). The cooling shell plate (11) is fixed to the cylinder body by multiple bolt connection groups (12) and forms the gap.

3. The temperature difference cooling equalizer for a steam turbine casing of a gas turbine unit according to claim 2, characterized in that, The nut portion of the bolt connection group (12) is welded and fixed to the outer peripheral wall of the cylinder body, and the bolt portion of the bolt connection group (12) is threaded onto the cooling shell plate (11).

4. The temperature difference cooling equalizer for a turbine casing of a gas turbine unit according to claim 2, characterized in that The cooling shell plate (11) is made of stainless steel and has an arc structure. The cooling shell plate (11) has flat steps (111) on both sides for installing the air intake pipe (2).

5. The temperature difference cooling equalizer for a steam turbine casing of a gas turbine unit according to claim 4, characterized in that The lower surface of the cooling shell plate (11) is provided with a heat-resistant coating (13).

6. The temperature difference cooling equalizer for a steam turbine casing of a gas turbine unit according to claim 2, characterized in that, The upper surface of the cooling shell plate (11), the outer peripheral wall of the air inlet pipe (2), and the outer peripheral wall of the exhaust pipe (3) are all provided with a heat insulation layer (6).

7. The temperature difference cooling equalizer for a turbine casing of a gas turbine unit according to claim 1, characterized in that The air supply system (4) includes a heat exchanger (41) using compressed air as the cooling medium. The heat exchanger (41) has an inlet pipe (42) and an outlet pipe (43) at its two ends. Both inlet pipes (2) are connected to the outlet pipe (43). A bypass pipe (44) is also provided between the inlet pipe (42) and the outlet pipe (43). The outlet pipe (43) is also provided with a switch ball valve (45), a regulating ball valve (46), a booster pump (47), and a temperature sensor (48) in sequence.

8. The temperature difference cooling equalizer for a steam turbine casing of a gas turbine unit according to claim 7, characterized in that The temperature sensor (48) is located between the two electrically controlled ball valves (5), and the booster pump (47) is located at the front end of the two air intake pipes (2).

9. The temperature difference cooling equalizer for a turbine casing of a gas turbine unit according to claim 7, characterized in that The inlet pipe (42) is also equipped with an inlet ball valve (421), the outlet pipe (43) is also equipped with an outlet ball valve (431), and the bypass pipe (44) is also equipped with a bypass ball valve (441).

10. The temperature difference cooling equalizer for a turbine casing of a gas turbine unit according to claim 7, characterized in that The outlet temperature of the heat exchanger (41) can be adjusted in the range of 50-450℃, the outlet pressure of the heat exchanger (41) is in the range of 0.4-0.8Mpa, and the flow rate of the heat exchanger (41) is in the range of 3-6m 3 / min.

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