Auxiliary pre-whirl nozzle with variable outlet air flow angle and gas turbine

Abstract

The present application provides an auxiliary pre-whirl nozzle with a variable outlet air flow angle and a gas turbine. The auxiliary pre-whirl nozzle (62) includes an adjusting vane (621) and an auxiliary nozzle flow passage (622). The adjusting vane (621) is arranged inside the auxiliary nozzle flow passage (622), and the adjusting vane (621) can rotate within the auxiliary nozzle flow passage (622) so as to change the direction of the gas ejected from the auxiliary pre-whirl nozzle (62).

Description

Technical Field

[0001] The present application relates to a gas turbine. Background Art

[0002] In a future power grid mainly based on renewable energy, a power generation gas turbine needs to have the ability of rapid start-up and rapid load change. In the marine field, the operating conditions of a marine gas turbine often change to meet the different navigation speed requirements of the ship. All of these require improving the efficiency of the gas turbine.

[0003] In order to make the gas turbine have a relatively high efficiency, the temperature at the inlet of the turbine moving blade will also be relatively high. In order to ensure the service life and reliability of the gas turbine, it is necessary for the pre-whirl nozzle to provide sufficient cold air to the turbine moving blade under various operating conditions.

[0004] In a possible technology, since the outlet angle of the main pre-whirl nozzle of the gas turbine is fixed. When the gas turbine is at a partial speed, especially below 60% of the maximum speed, the circumferential velocity difference between the airflow ejected from the main pre-whirl nozzle and the turntable is relatively large, the inlet attack angle at the turntable receiving hole is relatively large, and a relatively large-sized flow separation will be formed in the turntable receiving hole, resulting in a relatively large pressure loss. The separated flow generates relatively large-sized vortices in the turntable receiving hole, significantly blocking the turntable receiving hole, and significantly reducing the air supply capacity of the nozzle to the turbine moving blade.

[0005] In another possible technology, the gas turbine has an auxiliary pre-whirl nozzle, and the auxiliary pre-whirl nozzle can provide additional cold air to the turntable receiving hole under some operating conditions, so that the turbine moving blade of the gas turbine can be fully cooled under some operating conditions. However, when there is over-whirl of the airflow (the tangential velocity of the nozzle airflow at the same radius is greater than the turntable speed) or under-whirl of the airflow (the tangential velocity of the nozzle airflow at the same radius is less than the turntable speed), the attack angle of the turntable receiving hole will increase significantly, increasing the pressure loss and resulting in an obvious decrease in the flow coefficient. Summary of the Invention

[0006] The present application aims to propose an auxiliary pre-whirl nozzle with a variable outlet airflow angle and a gas turbine, and the auxiliary pre-whirl nozzle enables the gas turbine to have a relatively high flow coefficient of the turntable receiving hole under various operating conditions and can provide sufficient cold air to the turbine moving blade.

[0007] An embodiment of the present application proposes an auxiliary pre-whirl nozzle with a variable outlet airflow angle, which includes an adjusting vane and an auxiliary nozzle flow passage. The adjusting vane is arranged inside the auxiliary nozzle flow passage, and the adjusting vane can rotate inside the auxiliary nozzle flow passage, thereby changing the direction of the gas ejected from the auxiliary pre-whirl nozzle.

[0008] In at least one possible implementation, the auxiliary pre-whirl nozzle includes a base, the adjusting vane is connected to the base, a distal end of the adjusting vane away from the base forms a tip, and the tip extends to an inner wall of the auxiliary nozzle flow passage.

[0009] In at least one possible implementation, the auxiliary nozzle flow passage extends spirally, and a spiral angle of the auxiliary nozzle flow passage is 10° to 20°.

[0010] In at least one possible implementation, a sealing ring is sleeved on the base, and the sealing ring is pressed against the inner wall of the auxiliary nozzle flow passage.

[0011] An embodiment of the present application further provides a gas turbine, which includes:

[0012] A stator disk;

[0013] A rotor disk, the rotor disk is arranged downstream of the stator disk, the rotor disk can rotate relative to the stator disk, and a turbine disk cavity is formed between the stator disk and the rotor disk;

[0014] A plurality of turbine moving blades, the plurality of turbine moving blades are uniformly arranged along the circumference of the rotor disk, the turbine moving blades are provided with inner cavities, the rotor disk is provided with rotor disk receiving holes, and the rotor disk receiving holes communicate the turbine disk cavity and the inner cavities of the turbine moving blades; and

[0015] A plurality of nozzles, the plurality of nozzles are arranged along the circumference of the stator disk and are provided on the stator disk, the nozzles include the auxiliary pre-whirl nozzle according to any one of the above technical solutions, and the auxiliary nozzle flow passage communicates with the turbine disk cavity.

[0016] In at least one possible implementation, the rotor disk receiving holes are inclined with respect to the axis of the gas turbine, and an upstream end of the rotor disk receiving holes is closer to the radial inner side than a downstream end.

[0017] In at least one possible implementation, a downstream end of the auxiliary pre-whirl nozzle is located radially inside an upstream end of the rotor disk receiving holes.

[0018] In at least one possible implementation, the turbine disk cavity includes a pre-whirl inlet disk cavity and an outer disk cavity, the rotor disk receiving holes and the nozzles are both communicated with the pre-whirl inlet disk cavity, the outer disk cavity is located radially outside the pre-whirl inlet disk cavity, and the outer disk cavity separates the pre-whirl inlet disk cavity from an area where the turbine moving blades are located.

[0019] In at least one possible implementation, the stator disk and / or the rotor disk are provided with a pre-whirl cavity sealing portion and a rim sealing portion, and the pre-whirl cavity sealing portion and the rim sealing portion define the outer disk cavity.

[0020] In at least one possible embodiment, the nozzle further includes a main pre-swirl nozzle, and the auxiliary pre-swirl nozzle is located radially outside the main pre-swirl nozzle, and the angles of the nozzle flow channels of the main pre-swirl nozzle and the auxiliary pre-swirl nozzle at the same circumferential position are different.

[0021] In at least one possible embodiment, the gas turbine further includes a casing that surrounds the stationary disk, the rotating disk, and the turbine moving blades. The auxiliary pre-swirl nozzle includes a base, the adjusting blade is connected to the base, and the base is connected with a stud, and the stud passes through the casing.

[0022] By adopting the above technical solution, the gas turbine using the auxiliary pre-swirl nozzle of the present application can, when the rotational speed is relatively low, adjust the deflection angle of the adjusting blade of the auxiliary pre-swirl nozzle to make the jet flow of the auxiliary pre-swirl nozzle fully mix with the swirl flow in the disk cavity, reduce the inlet attack angle of the mixed air flow at the rotating disk receiving hole, reduce the pressure loss, improve the ability of the nozzle to supply cold air to the turbine moving blades through the rotating disk receiving hole, and improve the service life and reliability of the turbine moving blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 FIG. shows a schematic structural diagram of a gas turbine according to an embodiment of the present application.

[0024] Figure 2 FIG. shows a schematic structural diagram of the auxiliary pre-swirl nozzle (non-deflected state) of the gas turbine according to an embodiment of the present application.

[0025] Figure 3 FIG. shows a schematic structural diagram of the auxiliary pre-swirl nozzle (deflected state) of the gas turbine according to an embodiment of the present application.

[0026] DESCRIPTION OF THE REFERENCE NUMERALS

[0027] 1 Casing

[0028] 2 Stationary disk

[0029] 3 Rotating disk 31 Pre-swirl cavity seal part 32 Rim seal part 33 Rotating disk receiving hole 34 Moving blade inlet air flow path

[0030] 4 Turbine guide vane

[0031] 5 Turbine moving blade

[0032] 6 Nozzle 61 Main pre-swirl nozzle 62 Auxiliary pre-swirl nozzle

[0033] 621 Adjusting blade 622 Auxiliary nozzle flow channel 623 Base 624 Sealing ring 625 Mounting hole

[0034] 7 Turbine disk cavity 71 Pre-whirl intake disk cavity 72 Outer disk cavity

[0035] 8 Stud

[0036] A Axial R Radial Detailed implementation manners

[0037] In order to more clearly elaborate the above-mentioned objects, features and advantages of the present application, the detailed implementation manners of the present application will be described in detail in this part in conjunction with the accompanying drawings. In addition to the various implementation manners described in this part, the present application can also be implemented in other different ways. Without departing from the spirit of the present application, those skilled in the art can make corresponding improvements, deformations and replacements. Therefore, the present application is not limited by the specific embodiments disclosed in this part. The protection scope of the present application shall be subject to the claims.

[0038] As Figures 1 to 3 shown, the implementation manner of the present application provides an auxiliary pre-whirl nozzle with variable outlet air flow angle and a gas turbine. The gas turbine includes a casing 1, a stationary disk 2, a rotating disk 3, turbine guide vanes 4, turbine rotor blades 5, nozzles 6 and studs 8.

[0039] The casing 1 can be cylindrical, and the casing 1 can surround the stationary disk 2, the rotating disk 3, the turbine guide vanes 4 and the turbine rotor blades 5.

[0040] The stationary disk 2 is stationary relative to the casing 1, and the rotating disk 3 is rotatably connected to the hub relative to the stationary disk 2. The stationary disk 2 is located on the upstream side of the rotating disk 3 ( Figure 1 the left side in

[0041] ). A plurality of turbine guide vanes 4 and a plurality of turbine rotor blades 5 can be provided. The plurality of turbine guide vanes 4 can be connected to the stationary disk 2 along the circumferential direction of the stationary disk 2 in a uniformly arranged manner, and the plurality of turbine rotor blades 5 can be connected to the rotating disk 3 along the circumferential direction of the rotating disk 3 in a uniformly arranged manner.

[0042] The space between the stationary disk 2 and the rotating disk 3 forms a turbine disk cavity 7. The turbine disk cavity 7 is annular. The turbine disk cavity 7 includes a pre-whirl intake disk cavity 71 and an outer disk cavity 72. The outer disk cavity 72 is located radially outside the pre-whirl intake disk cavity 71.

[0043] The number of the turntable receiving holes 33 may be the same as the number of the turbine moving blades 5, and the number of the moving blade inlet gas flow paths 34 may be the same as the number of the turbine moving blades 5.

[0044] The stationary disk 2 and / or the turntable 3 may be provided with a pre-whirl chamber seal portion 31 and a rim seal portion 32. The pre-whirl chamber seal portion 31 may be located radially inside the rim seal portion 32, and the pre-whirl chamber seal portion 31 and the rim seal portion 32 define an outer disk chamber 72.

[0045] In the present embodiment, both the stationary disk 2 and the turntable 3 are provided with a pre-whirl chamber seal portion 31 and a rim seal portion 32. The pre-whirl chamber seal portion 31 includes a toothed structure protruding in opposite directions, and the rim seal portion 32 includes a flange structure protruding in opposite directions.

[0046] In the radial direction R of the gas turbine, the pre-whirl chamber seal portion 31 is located between the pre-whirl inlet disk chamber 71 and the outer disk chamber 72, and the rim seal portion 32 is located at the radially outer portion of the outer disk chamber 72. The pre-whirl chamber seal portion 31 can prevent the gas in the pre-whirl inlet disk chamber 71 from easily entering the outer disk chamber 72, but is prone to flow toward the turntable receiving holes 33. The outer disk chamber 72 can separate the pre-whirl inlet disk chamber 71 from the area where the turbine moving blades 5 are located, preventing the high-temperature gas in the area where the turbine moving blades 5 are located from entering the pre-whirl inlet disk chamber 71, thereby avoiding affecting the cooling of the gas in the pre-whirl inlet disk chamber 71 on the turbine moving blades 5.

[0047] A plurality of nozzles 6 are arranged on the stationary disk 2 in a circumferentially uniform manner. The upstream end of the nozzle 6 communicates with the compressor, the downstream end of the nozzle 6 communicates with the pre-whirl inlet disk chamber 71, and the gas ejected from the nozzle 6 can flow from the pre-whirl inlet disk chamber 71 to the turntable receiving holes 33.

[0048] The nozzle 6 includes a main pre-whirl nozzle 61 and an auxiliary pre-whirl nozzle 62. The number of the main pre-whirl nozzles 61 may be the same as the number of the turntable receiving holes 33, and the number of the auxiliary pre-whirl nozzles 62 may be the same as the number of the turntable receiving holes 33.

[0049] The auxiliary pre-whirl nozzle 62 may be located radially outside the main pre-whirl nozzle 61. The nozzle flow path angles of the main pre-whirl nozzle 61 and the auxiliary pre-whirl nozzle 62 at the same circumferential position may be different, and the main pre-whirl nozzle 61 and the auxiliary pre-whirl nozzle 62 at the same circumferential position can eject gas in different directions. Valves may be respectively provided upstream of the main pre-whirl nozzle 61 and the auxiliary pre-whirl nozzle 62, and the flow rates of the main pre-whirl nozzle 61 and the auxiliary pre-whirl nozzle 62 can be controlled through their respective valves. For example, the flow rate of the auxiliary pre-whirl nozzle 62 may not exceed 10% of the sum of the flow rates of the main pre-whirl nozzle 61 and the auxiliary pre-whirl nozzle 62.

[0050] The downstream end of the auxiliary pre-whirl nozzle 62 can be located radially inside the upstream end of the turntable receiving hole 33, and the air flow ejected from the auxiliary pre-whirl nozzle 62 can easily enter the turntable receiving hole 33.

[0051] The auxiliary pre-whirl nozzle 62 includes an adjusting vane 621, an auxiliary nozzle flow passage 622, a base 623, a sealing ring 624, and a mounting hole 625.

[0052] The auxiliary nozzle flow passage 622 penetrates the stationary disk 2 along the axial direction A of the gas turbine, and the auxiliary nozzle flow passage 622 extends spirally. The gas ejected from the auxiliary pre-whirl nozzle 62 has a certain angle and is not along the axial direction A of the gas turbine. The spiral lead angle of the auxiliary nozzle flow passage 622 can be 10° to 20°.

[0053] The adjusting vane 621 can be connected to the base 623. The adjusting vane 621 is located inside the auxiliary nozzle flow passage 622, and by rotating the base 623, the adjusting vane 621 can be rotated inside the auxiliary nozzle flow passage 622.

[0054] The mounting hole 625 is provided on the base 623. The mounting hole 625 can be a threaded hole. The mounting hole 625 mounts the stud 8. The stud 8 can pass through the casing 1 and be connected to a deflection mechanism (not shown). The deflection mechanism can drive the stud 8 to rotate. By the action of the deflection mechanism, the adjusting vane 621 can be rotated, thereby adjusting the angle of the gas ejected from the auxiliary pre-whirl nozzle 62.

[0055] As Figure 2 shown, the adjusting vane 621 is in an undeflected state. The inclination angle of the adjusting vane 621 is approximately equal to the spiral lead angle of the auxiliary nozzle flow passage 622. The sheet-like adjusting vane 621 hardly blocks the auxiliary nozzle flow passage 622, and the opening of the auxiliary nozzle flow passage 622 is the largest. The air flow can be ejected along the extending direction of the auxiliary nozzle flow passage 622.

[0056] As Figure 3 shown, the adjusting vane 621 is in a deflected state. The adjusting vane 621 can partially block the auxiliary nozzle flow passage 622, and the adjusting vane 621 can affect the direction of the air flow ejected from the auxiliary nozzle flow passage 622.

[0057] The adjusting vane 621 can be located in the downstream part of the auxiliary nozzle flow passage 622. The adjusting vane 621 can guide the flow direction of the air flow, so that the air flow ejected from the auxiliary pre-whirl nozzle 62 can adjust the ejection angle according to the rotational speed of the gas turbine, thereby reducing the tangential velocity of the mixed air flow after the jet flow of the nozzle 6 is mixed with the swirl in the pre-whirl intake disk cavity 71, reducing the intake attack angle at the turntable receiving hole 33, and improving the ability of the nozzle 6 to supply cold air to the turbine moving blade 5 through the turntable receiving hole 33.

[0058] Adjusting the distal end of the adjusting vane 621 away from the base 623 can form a tip, and the tip can extend to the inner wall of the auxiliary nozzle flow passage 622, so that when the adjusting vane 621 deflects, the contact between the distal end of the adjusting vane 621 and the inner wall of the auxiliary nozzle flow passage 622 is less. For example, the adjusting vane 621 can be a sheet-like triangle, and one of the angles serves as the distal end of the adjusting vane 621.

[0059] In this embodiment, the adjusting vane 621 can be a flat sheet. In other possible embodiments, the adjusting vane can also be a sheet formed by a curved surface. The shape of the adjusting vane can be adapted to the spiral angle of the auxiliary nozzle flow passage 622, so that when the adjusting vane is fully opened, the blocking of the air flow by the adjusting vane is less.

[0060] The sealing ring 624 is sleeved on the base 623. The sealing ring 624 can be pressed against the inner wall of the auxiliary nozzle flow passage 622, and the sealing ring 624 can prevent the gas in the auxiliary nozzle flow passage 622 from leaking from the position of the base 623.

[0061] The auxiliary pre-whirl nozzle 62 can be closed when the gas turbine is at a relatively high speed. For example, when the gas turbine is in a working condition above 60% of the maximum speed, the valve connected to the auxiliary pre-whirl nozzle 62 is closed, and only by jetting air through the main pre-whirl nozzle 61 can the flow coefficient of the rotary table receiving hole 33 meet the requirements.

[0062] Compared with the auxiliary pre-whirl nozzle with a non-adjustable angle, when the gas turbine is at 30% of the maximum speed, the blade deflection angle of the auxiliary nozzle can be 45° (the deflection direction is the direction of reducing the tangential velocity of the air flow). According to the numerical simulation results, the pressure loss of the rotary table receiving hole 33 can be reduced by 33.4%, the inlet attack angle can be reduced by 6.9°, the flow coefficient of the rotary table receiving hole 33 can be increased by 3.5%, and the cooling effect on the turbine moving blade is improved.

[0063] Compared with the auxiliary pre-whirl nozzle with a non-adjustable angle, when the gas turbine is at 50% of the maximum speed, the blade deflection angle of the auxiliary nozzle can be 29° (the deflection direction is the direction of reducing the tangential velocity of the air flow). According to the numerical simulation results, the pressure loss of the rotary table receiving hole 33 can be reduced by 14.2%, the inlet attack angle can be reduced by 2.1°, the flow coefficient of the rotary table receiving hole 33 can be increased by 1.6%, and the cooling effect on the turbine moving blade is improved.

[0064] The gas turbine of the present application can, when the speed is relatively low, adjust the deflection angle of the adjusting vane of the auxiliary pre-whirl nozzle 62 to make the jet flow of the auxiliary pre-whirl nozzle 62 mix fully with the swirl flow of the disk cavity, reduce the inlet attack angle of the mixed air flow at the rotary table receiving hole 33, reduce the pressure loss, improve the ability of the nozzle to supply cold air to the turbine moving blade 5 through the rotary table receiving hole 33, and improve the service life and reliability of the turbine moving blade 5.

[0065] It should be understood that at least some aspects or features of the above embodiments, examples or illustrations can be appropriately combined.

[0066] It can be understood that in this application, when the number of components or members is not specifically limited, the number can be one or more, and here "more than one" means two or more. For the case where the number of components or members shown in the drawings and / or described in the specification is a specific number such as two, three, four, etc., this specific number is usually exemplary rather than restrictive, and it can be understood as more than one, that is, two or more. However, this does not mean that this application excludes the case of one.

[0067] In this application, unless otherwise clearly stated or limited, terms such as "install", "assemble", "connect", "link", "join", "fasten", "abut", "communicate", "conduct", etc. should be understood in a broad sense. For example, it can be direct or indirect. For example, regarding connection, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components, unless otherwise clearly stated or limited. For example, regarding communication / conductivity, etc., it can be directly communicated / conducted or indirectly communicated / conducted via an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0068] In this application, unless otherwise clearly stated or limited, a component being arranged / installed / located / accommodated / placed in another component can be any of the following two situations: a part or most of this component is located inside the other component; and this component is completely accommodated inside the other component.

[0069] Although the above embodiments are used to describe this application in detail, for those skilled in the art, this application is obviously not limited to the embodiments described in this specification. This application can be modified and implemented as a variant embodiment without departing from the gist and scope of this application determined by the claims. Therefore, the descriptions in this specification are for illustrative purposes and do not have any restrictive meaning for this application.

Claims

1. An auxiliary pre-whirl nozzle with a variable outlet airflow angle, characterized in that, It includes an adjusting vane (621) and an auxiliary nozzle passage (622). The adjusting vane (621) is arranged inside the auxiliary nozzle passage (622), and the adjusting vane (621) can rotate within the auxiliary nozzle passage (622) so as to change the direction of the gas ejected from the auxiliary pre-whirl nozzle (62). The auxiliary pre-whirl nozzle (62) includes a base (623). The adjusting vane (621) is connected to the base (623). The distal end of the adjusting vane (621) away from the base (623) forms a tip, and the tip extends to the inner wall of the auxiliary nozzle passage (622). The auxiliary nozzle passage (622) extends spirally, and the spiral lead angle of the auxiliary nozzle passage (622) is 10° to 20°.

2. The auxiliary pre-whirl nozzle with variable outlet airflow angle according to claim 1, characterized in that A sealing ring (624) is sleeved on the base (623), and the sealing ring (624) is pressed against the inner wall of the auxiliary nozzle passage (622).

3. A gas turbine, characterized in that, It includes: a stationary disk (2); a rotating disk (3) which is arranged downstream of the stationary disk (2). The rotating disk (3) can rotate relative to the stationary disk (2), and a turbine disk cavity (7) is formed between the stationary disk (2) and the rotating disk (3); a plurality of turbine moving blades (5) which are uniformly arranged along the circumference of the rotating disk (3). The turbine moving blades (5) are provided with inner cavities, and the rotating disk (3) is provided with a rotating disk receiving hole (33). The rotating disk receiving hole (33) communicates the turbine disk cavity (7) and the inner cavity of the turbine moving blade (5); and a plurality of nozzles (6) which are arranged along the circumference of the stationary disk (2) and arranged on the stationary disk (2). The nozzle (6) includes the auxiliary pre-whirl nozzle (62) described in claim 1 or 2, and the auxiliary nozzle passage (622) communicates with the turbine disk cavity (7).

4. The gas turbine according to claim 3, characterized in that, The rotating disk receiving hole (33) is inclined with respect to the axial direction (A) of the gas turbine, and the upstream end of the rotating disk receiving hole (33) is closer to the radial inner side than the downstream end.

5. The gas turbine according to claim 3, characterized in that, The downstream end of the auxiliary pre-whirl nozzle (62) is located radially inside the upstream end of the rotating disk receiving hole (33).

6. The gas turbine according to claim 3, characterized in that, The turbine disk cavity (7) includes a pre-whirl intake disk cavity (71) and an outer disk cavity (72). The rotating disk receiving hole (33) and the nozzle (6) both communicate with the pre-whirl intake disk cavity (71). The outer disk cavity (72) is located radially outside the pre-whirl intake disk cavity (71), and the outer disk cavity (72) separates the pre-whirl intake disk cavity (71) from the area where the turbine moving blade (5) is located.

7. The gas turbine according to claim 6, characterized in that, The stationary disk (2) and / or the rotating disk (3) is provided with a pre-whirl cavity sealing portion (31) and a rim sealing portion (32), and the pre-whirl cavity sealing portion (31) and the rim sealing portion (32) define the outer disk cavity (72).

8. The gas turbine according to claim 3, characterized in that, The nozzle (6) further includes a main pre-swirl nozzle (61), and the auxiliary pre-swirl nozzle (62) is located radially outside the main pre-swirl nozzle (61). The angles of the nozzle flow passages of the main pre-swirl nozzle (61) and the auxiliary pre-swirl nozzle (62) at the same circumferential position are different.

9. The gas turbine according to claim 3, characterized in that, The gas turbine further includes a casing (1), the casing (1) surrounds the stator disc (2), the rotor disc (3) and the turbine moving blade (5). The auxiliary pre-swirl nozzle (62) includes a base (623), the adjusting blade (621) is connected to the base (623), and a stud (8) is connected to the base (623), and the stud (8) passes through the casing (1).

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