Pre-swirl nozzle structure and gas turbine

Abstract

The utility model belongs to the technical field of gas turbines, and particularly discloses a pre-swirl nozzle structure and a gas turbine. The pre-whirl nozzle structure comprises a stationary blade sealing ring and a plugging piece, the stationary blade sealing ring is annular, a plurality of pre-whirl channels are formed in the circumferential direction of the stationary blade sealing ring at intervals, and the pre-whirl channels are divided into common channels and standby channels; and the plugging piece is detachably arranged in each standby channel. The flow can be adjusted by opening or closing the standby channel, the standby channel is plugged through the plugging piece, and the plugging piece is detachably arranged in the standby channel. When the standby channel needs to be opened, the plugging piece is detached; when the standby channel needs to be closed, the plugging piece is installed in the standby channel, the pre-swirl nozzle structure cannot be damaged, the pre-swirl flow can be conveniently adjusted, and adjustment is convenient.

Description

Technical Field

[0001] The utility model belongs to the technical field of gas turbines, and in particular relates to a pre-swirl nozzle structure and a gas turbine. Background Art

[0002] As the operating temperature of turbine blades increases, the amount of cooling air used has reached between 20% and 30% of the compressor inlet air flow. In order to reduce the amount of cooling air used and increase the power of aircraft engines or gas turbines, a pre-swirl system can be used to reduce the temperature of the cold air used to cool the turbine blades. The basic principle of pre-swirl is to generate a circumferential velocity in the direction of rotation of the impeller for the cooling air before entering the blades, thereby reducing the relative total temperature between the cooling air and the turbine blades. From the perspective of energy exchange, pre-swirl can reduce the amount of work done by the turbine blades on the cooling air, thereby reducing its total temperature. If the pre-swirl system flow is found to be insufficient during the test process after the gas turbine is assembled, the pre-swirl system needs to be improved to adjust the pre-swirl flow.

[0003] The pre-swirl nozzle structure in the related art changes the cross-sectional area of ​​the airflow and adjusts the flow rate by twisting and grinding the swirl blades or by twisting and surfacing. The twisting and grinding of the swirl blades will cause irreparable damage to the swirl blades and have low efficiency. The twisting and surfacing will affect the strength of the surrounding structure, and the surfacing accuracy is difficult to ensure, which will affect the uniformity of the airflow. Summary of the invention

[0004] The utility model aims to solve one of the technical problems in the related art at least to a certain extent. To this end, the embodiment of the utility model proposes a pre-swirl nozzle structure, which can facilitate the adjustment of the pre-swirl flow rate and is easy to adjust.

[0005] The embodiment of the utility model also provides a gas turbine.

[0006] The pre-swirl nozzle structure of the embodiment of the utility model includes: a stationary blade sealing ring, which is annular, and has a plurality of pre-swirl channels arranged at circumferential intervals along the stationary blade sealing ring, and the pre-swirl channels are divided into common channels and spare channels; a sealing member, and the sealing member is detachably arranged in each of the spare channels.

[0007] In this embodiment, according to the design analysis, the flow rate of the common channel can usually meet the cooling gas demand. Under normal circumstances, the common channel is in an open state and the spare channel is in a closed state. However, when the flow test value is larger than the design value or smaller than the preset value, the flow rate can be adjusted by opening or closing the spare channel. The spare channel is blocked by a blocking piece, and the blocking piece is detachably arranged in the spare channel. When the spare channel needs to be opened, the blocking piece is removed; when the spare channel needs to be closed, the blocking piece is installed in the spare channel, which will not cause damage to the pre-swirl nozzle structure and is easy to adjust.

[0008] In this embodiment, the spare channel is a threaded hole, the blocking member is a screw or a bolt, and the blocking member is threadedly connected to the spare channel.

[0009] In this embodiment, the total flow area of ​​the plurality of pre-swirl channels is A, the flow area of ​​the standby channel is B, and B=5% to 30%A.

[0010] In this embodiment, the aspect ratio of the pre-spin channel is C, where C>2.

[0011] In this embodiment, the angle between the pre-swirl channel and the radial direction of the stationary blade sealing ring is α, and α is 10° to 65°.

[0012] In this embodiment, the inlet of the pre-swirl channel is provided with a chamfer.

[0013] In this embodiment, a plurality of the standby channels and a plurality of the common channels are provided, and the plurality of the standby channels and the plurality of the common channels are arranged alternately.

[0014] In this embodiment, the plurality of spare channels are evenly spaced between the plurality of common channels.

[0015] A gas turbine comprises the above-mentioned pre-swirl nozzle structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of a pre-spin system according to an embodiment of the utility model.

[0017] Figure 2 It is a partial cross-sectional structural schematic diagram of the pre-swirl nozzle structure of an embodiment of the utility model.

[0018] Reference numerals:

[0019] 1. Pre-swirl nozzle structure; 101. Stator blade sealing ring; 102. Sealing piece; 103. Pre-swirl channel; 1031. Common channel; 1032. Spare channel; 104. First flange; 105. Second flange; 2. Wheel disc; 3. Mini disc; 4. Turbine stator blade; 5. Turbine moving blade; 6. Rim sealing part; 7. U-shaped ring cavity; 8. Sealing assembly; 9. Rotor-static cavity; 10. Pre-swirl cavity; 11. Receiving hole; 12. Cover plate cavity; 13. Air supply channel. DETAILED DESCRIPTION

[0020] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but cannot be understood as limiting the present invention.

[0021] In this embodiment, if Figure 2 As shown, the pre-swirl nozzle structure 1 includes a stationary blade sealing ring 101 and a sealing member 102. The stationary blade sealing ring 101 is annular, and a plurality of pre-swirl channels 103 are arranged at circumferential intervals along the stationary blade sealing ring 101. The pre-swirl channels 103 are divided into a common channel 1031 and a spare channel 1032; and a sealing member 102 is detachably arranged in each spare channel 1032.

[0022] It should be noted that, according to the design analysis, the flow of the common channel 1031 can usually meet the cooling gas demand. Under normal circumstances, the common channel 1031 is in an open state and the spare channel 1032 is in a closed state. However, when the flow test value is larger than the design value or smaller than the preset value, the flow can be adjusted by opening or closing the spare channel 1032. The spare channel 1032 is blocked by the blocking member 102, and the blocking member 102 is detachably arranged in the spare channel 1032. When the spare channel 1032 needs to be opened, the blocking member 102 is removed; when the spare channel 1032 needs to be closed, the blocking member 102 is installed in the spare channel 1032, which will not cause damage to the pre-swirl nozzle structure 1 and is easy to adjust.

[0023] In this embodiment, the spare channel 1032 is a threaded hole, the blocking member 102 is a screw or a bolt, and the blocking member 102 is threadedly connected to the spare channel 1032 .

[0024] Specifically, the common channels 1031 may also be set as threaded holes. When the flow test value is larger than the design value and exceeds a preset value, the blocking member 102 may be used to block a certain number of the common channels 1031 .

[0025] It is understandable that by setting the blocking member 102 as a screw or bolt and the spare channel 1032 as a threaded hole, the blocking member 102 and the spare channel 1032 can be connected by threading, and the blocking member 102 can be installed on the stationary blade sealing ring 101 or removed from the stationary blade sealing ring 101 by rotating the blocking member 102, so that the connection between the blocking member 102 and the stationary blade sealing ring 101 is more convenient. Of course, the blocking member 102 and the spare channel 1032 can also be detachably connected in other ways, which are not limited here.

[0026] In this embodiment, the total flow area of ​​the plurality of pre-swirl channels 103 is A, and the flow area of ​​the standby channel 1032 is B, where B=5% to 30%A.

[0027] For example, the flow area of ​​the spare channel 1032 can be 5%A, 8%A, 10%A, 12%A, 15%A, 17%A, 20%A, 23%A, 25%A, 27%A or 30%A, etc. If the flow through the spare channel 1032 is too small, it will not be enough to compensate when the flow test value is smaller than the design value by more than the preset value. If the flow area of ​​the spare channel 1032 is too large, it will affect the layout space of the common channel 1031, making it inconvenient to set up the common channel 1031.

[0028] It should be noted that by setting the flow area of ​​the spare channel 1032 to 5% to 30% of the flow area of ​​the common channel 1031 , the spare channel 1032 will not affect the arrangement of the common channel 1031 and is sufficient to compensate for the uncertainty of the design.

[0029] In this embodiment, the aspect ratio of the pre-spin channel 103 is C, where C>2.

[0030] For example, the aspect ratio of the pre-spin channel 103 may be 2.1, 2.2, 2.5, 2.8 or 3, etc. Of course, the aspect ratio of the pre-spin channel 103 may also be set to other values, which are not limited here.

[0031] The aspect ratio of the pre-swirl channel 103 is set to be greater than 2, so as to reduce the pressure loss and flow resistance of the pre-swirl nozzle.

[0032] In this embodiment, if Figure 2 As shown, the angle between the pre-swirl channel 103 and the radial direction of the stationary blade sealing ring 101 is α, and α is 10° to 65°.

[0033] For example, α can be 10°, 15°, 20°, 25°, 30°, 35°, 40°, 45°, 50°, 55°, 60° or 65°, etc. If the α value is too small, the cooling air pre-rotation will be insufficient, and the corresponding temperature drop will not be produced, and even the temperature rise will occur; if the α value is too large, the excessive pre-rotation speed will cause a large loss in the receiving hole 11, affecting the air supply pressure.

[0034] In this embodiment, by setting the inclination angle of the pre-swirl channel 103 to 10°~65°, the cooling gas can obtain a certain pre-swirl speed, which is beneficial to lowering the temperature of the cooling gas, and can also reduce the pressure loss of the cooling gas in the receiving hole 11, which is beneficial to stabilizing the gas supply pressure.

[0035] In this embodiment, the inlet of the pre-swirl channel 103 is provided with a chamfer.

[0036] Specifically, the chamfer may be a right angle or a rounded angle, and the form of the chamfer may be selected as required, which is not limited here.

[0037] By providing a chamfer at the inlet of the pre-swirl channel 103, the flow resistance of the inlet of the pre-swirl channel 103 to the cooling gas can be reduced, the pressure loss can be reduced, the air supply flow rate can be increased, and the air supply can be more sufficient.

[0038] In this embodiment, if Figure 2 As shown, a plurality of spare channels 1032 and a plurality of common channels 1031 are provided, and the plurality of spare channels 1032 and the plurality of common channels 1031 are arranged alternately.

[0039] The specific number of spare channels 1032 and common channels 1031 can be set according to actual design requirements and is not limited here.

[0040] It can be understood that the common channel 1031 is usually in an open state, and the spare channel 1032 is usually in a closed state. By staggering the spare channel 1032 and the common channel 1031, it is beneficial to make the airflow distribution more uniform.

[0041] In this embodiment, the plurality of spare channels 1032 are evenly spaced between the plurality of common channels 1031 .

[0042] Specifically, the plurality of spare channels 1032 are evenly spaced between the plurality of common channels 1031 , which means that the number of common channels 1031 between two adjacent spare channels 1032 is the same.

[0043] By evenly spacing the plurality of spare channels 1032 between the plurality of spare channels 1032 , the airflow distribution can be further made more uniform.

[0044] When the pre-swirl nozzle structure 1 in this embodiment is used, due to the design accuracy problem, the flow design value of the pre-swirl nozzle structure 1 often has a certain deviation from the experimental test value. When the flow design value of the pre-swirl nozzle structure 1 deviates from the experimental test value by ≤3%, no adjustment is made, that is, the common channel 1031 is opened and the spare channel 1032 is closed; when the flow test value of the pre-swirl nozzle structure 1 is smaller than the design value by more than 3%, a certain number of spare channels 1032 need to be opened, and the specific number is determined by the deviation size and the flow capacity calculation of a single pre-swirl channel 103, and the selected spare channels 1032 should be uniformly distributed in the circumferential direction; when the flow test value of the pre-swirl nozzle structure 1 is larger than the design value by more than 3%, a certain number of common channels 1031 need to be blocked by the blocking member 102, and the specific number is determined by the deviation size and the flow capacity calculation of a single channel, and the selected common channels 1031 should be uniformly distributed in the circumferential direction.

[0045] In this embodiment, a gas turbine is also provided, comprising the above-mentioned pre-swirl nozzle structure 1.

[0046] like Figure 1 As shown, the gas turbine further includes a wheel disc 2, a Mini disc 3, a turbine stator blade 4, and a turbine moving blade 5. The Mini disc 3 is arranged between two adjacent wheel discs 2, the pre-swirl nozzle structure 1 is arranged outside the Mini disc 3, the pre-swirl nozzle structure 1 is arranged outside the turbine stator blade 4, and the wheel disc 2 is arranged outside the turbine moving blade 5. The specific connection method of the wheel disc 2, the Mini disc 3, the turbine stator blade 4, and the turbine moving blade 5 is a conventional prior art, which will not be repeated here.

[0047] After the cooling air flows from the stator passage of the turbine stator blade 4 through the U-shaped annular cavity 7 to the pre-swirl nozzle, the flow direction changes and a circumferential velocity is generated along the direction of rotation of the wheel disc. Part of the cooling air flowing out of the pre-swirl passage 103 outlet leaks into the rotor-stator cavity 9 through the sealing assembly 8 between the pre-swirl nozzle structure 1 and the Mini disc 3 and the wheel disc 2, and then to the wheel rim sealing part 6 for wheel rim sealing. The remaining part enters the turbine rotor blade passage in the turbine rotor blade 5 through the pre-swirl cavity 10, the receiving hole 11, the cover plate cavity 12, and the air supply passage 13 to cool the turbine rotor blade 5.

[0048] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0049] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present utility model, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0050] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0051] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0052] In the present utility model, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0053] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations of the present invention. Ordinary technicians in the field can change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A pre-swirl nozzle structure, characterized in that: include: A stationary blade sealing ring, wherein the stationary blade sealing ring is annular, and a plurality of pre-swirl channels are arranged at intervals along the circumference of the stationary blade sealing ring, and the pre-swirl channels are divided into a common channel and a spare channel; A blocking piece is detachably provided in each of the spare channels.

2. The pre-swirl nozzle structure according to claim 1, characterized in that: The spare channel is a threaded hole, the blocking piece is a screw or a bolt, and the blocking piece is threadedly connected to the spare channel.

3. The pre-swirl nozzle structure according to claim 1, characterized in that: The total flow area of ​​the plurality of pre-swirl channels is A, the flow area of ​​the standby channel is B, and B=5% to 30%A.

4. The pre-swirl nozzle structure according to claim 1, characterized in that: The aspect ratio of the pre-spin channel is C, where C>2.

5. The pre-swirl nozzle structure according to claim 1, characterized in that: The angle between the pre-swirl channel and the radial direction of the stationary blade sealing ring is α, and α is 10° to 65°.

6. The pre-swirl nozzle structure according to claim 1, characterized in that: The inlet of the pre-swirl channel is provided with a chamfer.

7. The pre-swirl nozzle structure according to claim 1, characterized in that: A plurality of the backup channels and a plurality of the common channels are provided, and the plurality of the backup channels and the plurality of the common channels are arranged alternately.

8. The pre-swirl nozzle structure according to claim 7, characterized in that: The plurality of spare channels are evenly spaced and arranged between the plurality of common channels.

9. A gas turbine, characterized in that: The invention comprises the pre-swirl nozzle structure according to any one of claims 1 to 8.

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