CN115653756A

CN115653756A - But prewhirl ware subassembly of on-line adjustment flow

Info

Publication number: CN115653756A
Application number: CN202211085261.9A
Authority: CN
Inventors: 李志伟; 孙晓; 周涛; 郦进; 李超军
Original assignee: China United Heavy Gas Turbine Technology Co Ltd
Current assignee: China United Heavy Gas Turbine Technology Co Ltd
Priority date: 2022-09-06
Filing date: 2022-09-06
Publication date: 2023-01-31

Abstract

The invention discloses a prerotator component capable of adjusting flow on line, comprising: the air compressor exhaust diffuser comprises an air compressor exhaust diffuser inner ring (8), a rotating ring (2) and an adjusting and locking assembly (4), wherein the air compressor exhaust diffuser inner ring (8) is positioned on the inner side of the rotating ring (2), and the air compressor exhaust diffuser inner ring (8) is matched with the rotating ring (2) to form a plurality of flow channels; the adjusting and locking assembly (4) is connected with the rotating ring (2), and the flow areas of the plurality of flow channels are adjusted by adjusting the rotating angle of the rotating ring (2), so that the air flow quantity of the flow channels is adjusted. The flow of the flow channel can be conveniently adjusted through the prerotator assembly, the online adjustment of the air flow is realized, the gas turbine does not need to be stopped, and the normal work of the gas turbine is not influenced, so that the working efficiency is improved.

Description

But prewhirl ware subassembly of on-line adjustment flow

Technical Field

The invention relates to a gas turbine, in particular to a prerotator assembly capable of adjusting flow on line.

Background

When the gas turbine works, a prerotator is usually arranged in front of a turbine rotor blade, and the prerotator enables air to generate rotational flow in the same direction as the rotation direction of a rotor, so that the friction loss generated by airflow and the rotor is reduced. Heavy duty combustion engines typically achieve adjustments in the air flow through the preswirler by adding a plug screw at the preswirler orifice. If the flow needs to be adjusted and the machine is stopped, an operator enters the internal part of the combustion engine for treatment.

The patent CN110594198A discloses an air inlet pre-rotator with adjustable blade angles, which can widen the flow and the adjustment range of a supercharger compressor, the air inlet pre-rotator is arranged at an air inlet of the compressor of a turbocharger, and the air inlet pre-rotator comprises a hub, a wheel rim and a driving plate assembly which are coaxially arranged from inside to outside; the wheel rim is connected with the air inlet of the air compressor. One end of the hub is provided with a wheel head which is used for guiding flow and preventing the adjustable blade from moving along the axial direction of the hub; a plurality of adjustable blades are uniformly arranged in the circumferential direction of the hub, one ends of the adjustable blades are connected with the hub, and the other ends of the adjustable blades are connected with the shifting lever. The inlet gas prerotator disclosed in the patent CN110594198A widens the flow rate and the adjustment range of the compressor by the angle-adjustable blades, but the adjustment process involves many parts, and the compressor needs to be stopped during the adjustment process.

The present invention has been made in view of the above problems.

Disclosure of Invention

The invention mainly aims to provide a prerotator assembly capable of adjusting flow online so as to solve the problem that a gas turbine needs to be stopped when the flow is adjusted in the prior art.

To achieve the above object, according to one aspect of the present invention, there is provided a prerotator assembly capable of on-line flow rate adjustment, the prerotator assembly comprising: the inner ring of the exhaust diffuser of the gas compressor is positioned at the inner side of the rotating ring, and the inner ring of the exhaust diffuser of the gas compressor is matched with the rotating ring to form a plurality of flow channels; the adjusting and locking assembly is connected with the rotating ring, and the flow areas of the plurality of flow channels are adjusted by adjusting the rotating angle of the rotating ring, so that the air flow flux of the flow channels is adjusted. Because the adjusting and locking assembly is arranged outside the air compressor cylinder, the air flow flux of the flow channel can be adjusted only by driving the rotating ring to rotate, the gas turbine does not need to be stopped, and the flow can be adjusted on line. The flow of the pre-flow channel is adjusted through the pre-rotator assembly, on one hand, the pre-flow channel is convenient and fast, on the other hand, the air flow can be adjusted on line, a gas turbine does not need to be stopped, and the normal work of the gas turbine cannot be influenced.

Further, the flow passage comprises a first flow passage, the rotating ring is provided with a plurality of windows along the circumference, the inner ring of the compressor exhaust diffuser is provided with a plurality of chambers along the circumference, and the windows and the chambers form a plurality of first flow passages in the circumferential direction.

Further, the flow passage further includes a second flow passage downstream of the first flow passage, the second flow passage receiving air from the first flow passage.

Further, the first flow passage has a first flow area, the second flow passage has a second flow area, and a minimum of the first flow area and the second flow area defines the air flow volume.

Further, the window and the chamber are partially overlapped in the circumferential direction to form an overlapping portion with an opening degree L, the opening degree L is proportional to the rotation angle of the rotating ring, and the value of the first flow area increases with the increase of the value of the opening degree L.

Further, the value of the first flow area is proportional to the value of the opening L.

Further, the window is square.

Further, the plurality of flow passages are evenly distributed along the circumferential direction of the rotating ring.

Furthermore, the second flow channel is arranged on the inner ring of the compressor exhaust diffuser and extends from the first flow channel to the inner side of the inner ring of the compressor exhaust diffuser, and the second flow channel has a second flow through area.

Further, the second flow passage extends in a direction offset from a radial direction of the compressor exhaust diffuser to impart a pre-swirl to the gas flow. The direction of the second flow channel enables the air to generate rotational flow in the same direction as the rotation direction of the rotor, and therefore friction loss generated by the air flow and the rotor is reduced.

Further, as the value of the opening degree L increases, the value of the first flow area increases from being smaller than the second flow area to being larger than the second flow area. The flow capacity is determined by the minimum value of the first flow area and the second flow area.

Further, the second runner is a hole-type runner.

Further, the rotating ring is of two semi-ring structures.

Furthermore, the semi-ring structure is connected through a flange.

Furthermore, the adjusting and locking assembly comprises a connecting rod part, and the rotating ring is driven to rotate by the connecting rod part. The adjusting and locking component is arranged outside the air compressor cylinder, and the air flow flux of the flow channel can be adjusted only by driving the rotating ring to rotate, so that the gas turbine does not need to be stopped, and the flow can be adjusted on line.

Further, adjustment and locking subassembly still includes the locking part, through locking part locking connecting rod portion to the locking rotating ring.

The prerotator assembly capable of adjusting the flow on line has a simple structure, is convenient to adjust, realizes the on-line adjustment of the air flow of the flow channel under the condition of not stopping the work of the gas turbine, thus not influencing the normal work of the gas turbine and improving the work efficiency.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 shows a schematic of the construction of an on-line flow-regulating prerotator according to the present invention; and

FIG. 2 shows a first isometric view of FIG. 1 in accordance with the invention; and

fig. 3 shows the second isometric view of fig. 1 according to the invention.

Wherein the figures include the following reference numerals:

1. a flange; 2. a rotating ring; 3. a cylinder; 4. an adjustment and locking assembly;

5. a link section; 51. a crank; 52. a slider; 6. an inclined hole; 7. a window; 8. an inner ring of an exhaust diffuser of the compressor;

9. a chamber;

l, opening degree; w, width.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

The present invention is described in further detail below with reference to specific examples, which are not to be construed as limiting the scope of the invention as claimed. The term "comprising" when used indicates the presence of a feature but does not preclude the presence or addition of one or more other features; the terms "lateral," "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like are used to indicate an orientation or positional relationship based on that shown in the drawings for ease of description only, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the invention; furthermore, the terms "first," "second," and the like are used for distinguishing between different objects and not for describing a particular order.

In the description, it is to be noted that, unless expressly specified or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, as for example, they may be fixedly connected, detachably connected, or integrally connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art. In addition, in the description of the present invention, "a plurality" means two or more unless otherwise specified.

Heavy duty combustion engines typically have a prerotator assembly in front of the turbine rotor blades, which is a type of prerotator assembly that induces air to swirl in the same direction as the rotor, thereby reducing the friction loss between the air flow and the rotor. In order to realize the heavy combustion engine without stopping when adjusting the flow, the invention provides a prerotator assembly for adjusting the flow on line, which realizes the adjustment of the air flow of the prerotator without stopping the engine.

The invention discloses a prerotator assembly capable of adjusting flow online, which comprises a compressor exhaust diffuser inner ring 8, a rotating ring 2 and an adjusting and locking assembly 4, wherein the compressor exhaust diffuser inner ring 8 is positioned at the inner side of the rotating ring 2, and the compressor exhaust diffuser inner ring 8 is matched with the rotating ring 2 to form a plurality of flow channels. The circulation is used for circulating air, and the size of the flow area of the flow channel determines the air circulation quantity. If the air flow quantity is adjusted, the flow area of the flow channel needs to be adjusted. In order to realize the on-line adjustment of the flow area of the flow passage, the rotating ring 2 is provided with an adjusting and locking assembly 4. The adjusting and locking assembly 4 drives the rotating ring 2 to rotate, and the flow areas of the plurality of flow channels are adjusted by adjusting the rotating angle of the rotating ring 2, so that the air flow flux of the flow channels is adjusted. Because the adjusting and locking component 4 is arranged outside the air compressor cylinder 3, the air flow flux of the flow channel can be adjusted only by driving the rotating ring 2 to rotate, the gas turbine does not need to be stopped, and the flow can be adjusted on line. The flow of the flow channel can be conveniently adjusted through the prerotator assembly, the online adjustment of the air flow is realized, the gas turbine does not need to be stopped, and the normal work of the gas turbine is not influenced, so that the working efficiency is improved.

The plurality of flow passages are uniformly distributed along the circumferential direction of the rotating ring 2. The flow passage includes a first flow passage. Preferably, the flow passage further comprises a second flow passage located downstream of the first flow passage.

The first flow passage is formed by matching the rotating ring 2 with the exhaust diffuser of the compressor. The rotating ring 2 is provided with a plurality of equidistant windows 7 along the circumference, and the windows and a plurality of chambers 9 in the circumferential direction of an inner ring 8 of the compressor exhaust diffuser are arranged in a uniform staggered manner, so that a first flow passage is formed in the circumferential direction. The windows 7 and the chambers 9 are partially overlapped in the circumferential direction to form an overlapping portion with an opening degree L, the opening degree L is proportional to the rotation angle of the rotating ring 2, and the first flow area increases with the increase of the opening degree L.

In the case where the window 7 is square and the chamber 9 is rectangular, the first flow area is proportional to the opening degree, that is, the value of the first flow area is linear with the angle at which the rotating ring 2 rotates, and the prerotator flow area is proportional to the angle at which the rotating ring 2 rotates. The shape of the window 7 is not limited to a square shape, and may be an oval shape, a circular shape, or a special shape. Also, the shape of the chamber 9 is not limited to a fixed shape, and may be set to different shapes, such as a rectangular parallelepiped, a cylinder, etc., according to practical situations.

The second flow passage receives air from the first flow passage, and as shown in fig. 1, the second flow passage is disposed on the compressor exhaust diffuser inner ring 8, extends from the first flow passage to the inner side of the compressor exhaust diffuser inner ring 8, and the plurality of second flow passages are uniformly distributed along the circumferential direction of the rotating ring 2.

The second flow channel is a hole-shaped flow channel, has a second flow area, and extends along a direction deviating from the radial direction of the compressor exhaust diffuser, namely the second flow channel is an inclined hole 6 formed in an inner ring 8 of the compressor exhaust diffuser, so that airflow is rotated in advance. The hole opening direction of the inclined holes 6 enables air to generate rotational flow in the same direction as the rotation direction of the rotor, and therefore friction loss generated by the air flow and the rotor is reduced. The perspective views of fig. 2-3 show the cross-sectional shape of the oblique hole 6. The number, the aperture and the inclination angle of the inclined holes 6 are calculated by a secondary air system of the gas turbine according to the design characteristics of the gas turbine, and depend on the air flow demand, the pressure difference, the structure and the like of a specific scheme.

The flow capacity of the flow channel is defined by the minimum value of the areas of the first flow channel and the second flow channel. In the process of online flow adjustment, the opening L is adjusted by adjusting the rotation angle of the rotating ring 2. As the value of the opening degree L increases, the value of the first flow area increases from being smaller than the second flow area to being larger than the second flow area. For a flow channel consisting of a first flow channel and a second flow channel, the flow capacity is determined by the minimum of the first flow area and the second flow area, i.e. the minimum of the first flow area and the second flow area defines the air throughput.

As shown in fig. 1 to 3, for a single window 7, the flow area is determined by the opening L of the overlapping portion of the window 7 and the chamber 9 and the width W of the window 7, where the width of the window 7 is W, and the first flow area = L × W of the first flow passage. And for the second flow passage, the second flow area is equal to the cross-sectional area of the inclined hole 6.

In the case where the window 7 is square and the chamber 9 is rectangular, the air flow rate and the rotation angle of the rotating ring 2 are linearly controlled. Depending on the design characteristic requirements of the gas turbine, the air flow rate and the rotation angle of the rotating ring 2 may be required to have a nonlinear relationship. When the air flow flux and the rotation angle of the rotating ring 2 need to be in a nonlinear relationship, the non-linear relationship can be realized in different ways, for example, the opening L of different windows 7 can be different at the same rotation angle of the rotating ring 2; or the window 7 on the rotating ring 2 is in a non-square structure such as a circle, an ellipse and the like.

Wherein, the rotating ring 2 has two semi-ring structures, is connected by the flange 1 and can be fastened by screws. After the flange 1 is fastened, the rotating ring 2 is driven to move through the adjusting and locking assembly 4. The adjustment and locking assembly 4 includes a link portion 5, and a driving force is provided through the link portion 5 to drive the rotating ring 2 to rotate. The connecting rod part 5 penetrates through the cylinder 3, and the connecting rod part 5 is adjusted and locked outside the cylinder 3, so that the flow can be adjusted on line. The connecting rod part 5 in fig. 1 is a crank 51 and slider 52 mechanism, the crank 51 is bolted with the outer ring of the rotating ring 2, and the slider 52 drives the crank 51 to rotate clockwise or anticlockwise, so as to drive the rotating ring 2 to rotate clockwise or anticlockwise relative to the inner ring 8 of the compressor exhaust diffuser, and thus the opening L value is adjusted. In fig. 1, the slider 52 rotates the crank 51 clockwise, which coincides with the direction of the pre-rotation of the air flow caused by the oblique direction of the oblique hole 6.

The adjustment and locking assembly 4 further comprises a locking portion through which the link portion 5 is locked, thereby locking the rotating ring 2. After the rotation angle of the rotating ring 2 is preliminarily adjusted, the pressure gauge is used for measuring the air flow pressure of the corresponding point position to judge whether the rotation angle of the rotating ring 2 is adjusted in place, if the rotation angle is adjusted in place, the sliding block 52 is locked by the locking part, and after the position of the sliding block 52 is locked, the position of the rotating ring 2 is correspondingly locked, so that the air circulation capacity of the flow channel is locked. The design of the locking portion is various, and it is sufficient if the displacement of the slider 52 can be limited.

Because the relative motion of the rotating ring 2 and the compressor exhaust diffuser can cause corresponding abrasion, in order to reduce the abrasion, hard alloy can be sprayed on the contact surface of the rotating ring 2 and/or the compressor exhaust diffuser inner ring 8 to increase the lubrication and reduce the abrasion.

In fig. 1, the outer side of the rotating ring 2 is an air flow high pressure area, the inner side is an air flow low pressure area, and the inclined direction of the flow channel inclined hole 6 causes the air flow to rotate clockwise in advance. In order to reduce the friction loss, the link portion 5 needs to rotate the rotating ring 2 clockwise. If the inclined direction of the inclined hole 6 of the flow channel causes the air flow to rotate counterclockwise in advance, the link portion 5 needs to drive the rotating ring 2 to rotate counterclockwise. For the adjusting and locking assembly 4, besides the crank 51 and slider 52 mechanism, other mechanisms capable of converting a rotational motion into a linear motion, such as a worm gear structure, may be adopted.

As can be seen from the above description, the above-described embodiments of the present invention achieve the following technical effects: the prerotator component for online regulating the flow has simple structure and convenient regulation, realizes online regulation of the air flow of the flow passage under the condition of not stopping the work of the gas turbine, thereby not influencing the normal work of the gas turbine and improving the work efficiency.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A prerotator assembly for on-line flow regulation, said prerotator assembly comprising: the air compressor exhaust diffuser comprises an air compressor exhaust diffuser inner ring (8), a rotating ring (2) and an adjusting and locking assembly (4), wherein the air compressor exhaust diffuser inner ring (8) is located on the inner side of the rotating ring (2), and the air compressor exhaust diffuser inner ring (8) is matched with the rotating ring (2) to form a plurality of flow channels; the adjusting and locking assembly (4) is connected with the rotating ring (2), and the flow area of the flow channels is adjusted by adjusting the rotating angle of the rotating ring (2), so that the air flow quantity of the flow channels is adjusted.

2. The preswirler assembly of claim 1, wherein the flow path comprises a first flow path, the rotating ring (2) circumferentially has a plurality of windows (7), the compressor exhaust diffuser inner ring (8) circumferentially has a plurality of cavities (9), and the windows (7) and the cavities (9) circumferentially form the plurality of first flow paths.

3. The prerotator assembly of claim 2, wherein the flow channel further comprises a second flow channel downstream from the first flow channel, the second flow channel receiving air from the first flow channel.

4. The prerotator assembly of claim 3, wherein the first flow channel has a first flow area and the second flow channel has a second flow area, a minimum of the first flow area and the second flow area defining the air throughput.

5. Prerotator assembly according to claim 4, wherein the window (7) overlaps the chamber (9) in a circumferential direction forming an overlap of an opening degree L proportional to the rotation angle of the rotating ring (2), the value of the first flow area increasing with increasing value of the opening degree L.

6. The prerotator assembly of claim 5, wherein the value of the first flow area is proportional to the value of the opening L.

7. The prerotator assembly according to claim 6, wherein the window (7) is square.

8. The prerotator assembly according to any one of claims 1-7, wherein the plurality of flow channels are evenly distributed along the circumferential direction of the rotating ring (2).

9. The prerotator assembly according to any one of claims 3 to 7, wherein the second flow passage is disposed on the compressor exhaust diffuser inner ring (8) and extends from the first flow passage to an inner side of the compressor exhaust diffuser inner ring (8), and the second flow passage has a second flow passage area.

10. The preswirler assembly of claim 9, wherein the second flow path extends in a direction offset from a radial direction of the compressor exhaust diffuser to provide for preswirl flow.

11. The preswirler assembly of claim 10, wherein the first flow area increases in value from less than the second flow area to greater than the second flow area as a value of the opening L increases.

12. The prerotator assembly of claim 10, wherein the second flow passage is an orifice-type flow passage.

13. The prerotator assembly according to claim 12, wherein the rotating ring (2) is of two half-ring structures.

14. The assembly of claim 13, wherein the half-ring structures are connected by a flange (1).

15. Prerotator assembly according to claim 14, wherein the adjustment and locking assembly (4) comprises a link portion (5), through which link portion (5) the rotation ring (2) is driven in rotation.

16. The spinner assembly according to claim 15, characterized in that the adjustment and locking assembly (4) further comprises a locking portion by which the link portion (5) is locked, thereby locking the rotating ring (2).