CN108071492B - Gas turbine and pre-rotation flow dividing device thereof - Google Patents
Gas turbine and pre-rotation flow dividing device thereof Download PDFInfo
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- CN108071492B CN108071492B CN201711375297.XA CN201711375297A CN108071492B CN 108071492 B CN108071492 B CN 108071492B CN 201711375297 A CN201711375297 A CN 201711375297A CN 108071492 B CN108071492 B CN 108071492B
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- 238000007789 sealing Methods 0.000 claims description 24
- 230000002093 peripheral effect Effects 0.000 claims description 8
- 230000007423 decrease Effects 0.000 claims description 5
- 230000003068 static effect Effects 0.000 claims description 4
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 238000001816 cooling Methods 0.000 abstract description 10
- 239000007789 gas Substances 0.000 description 33
- 230000000903 blocking effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 230000000670 limiting effect Effects 0.000 description 3
- 230000000873 masking effect Effects 0.000 description 3
- 238000009987 spinning Methods 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 230000002452 interceptive effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000009545 invasion Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas turbine and a pre-rotation flow dividing device thereof, wherein the pre-rotation flow dividing device comprises an annular body, the annular body is provided with a plurality of pre-rotation channels, each pre-rotation channel is provided with an air inlet and an air outlet, a first end of the annular body is provided with a pneumatic hole communicated with the pre-rotation channel, a part of air flow entering the pre-rotation channel through the air inlet forms swirling flow and flows out of the pre-rotation channel through the air outlet, and the other part of air flow entering the pre-rotation channel through the air inlet flows out of the first end of the annular body through the pneumatic hole. The invention can control the flow distribution of cooling air by controlling the air outlet of the pre-rotation channel and the throttling area of the pneumatic hole, thereby avoiding the problem that the existing structure is easily affected by temperature and improving the accuracy and controllability of flow distribution.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a pre-rotation flow dividing device of a gas turbine and the gas turbine with the pre-rotation flow dividing device.
Background
In a gas turbine, the combustion gas generated in the combustion chamber is fed into the turbine to drive the turbine to rotate, and the first stage impeller of the turbine is in a high temperature environment due to the high temperature of the combustion gas, so that part of the air needs to be extracted from the compressor for cooling. In the related art, the distribution of the cooling air is mainly achieved through the diverter ring, specifically, the purpose of controlling the flow is achieved by controlling the sealing gap between the diverter ring and the stationary member.
However, in the above form, the seal clearance is greatly affected by the disk and stationary member temperature distribution, reducing the accuracy and controllability of the cooling air flow distribution.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems in the related art to some extent.
To this end, one aspect of the present invention proposes a pre-rotation splitting device for a gas turbine that improves the accuracy and controllability of the cooling air flow distribution.
In another aspect, the invention also provides a gas turbine.
The pre-rotation splitting device of the gas turbine according to the embodiment of the first aspect of the present invention includes: the annular body is provided with a plurality of pre-rotation channels, each pre-rotation channel is provided with an air inlet and an air outlet, a first end of the annular body is provided with a pneumatic hole communicated with the pre-rotation channel, wherein part of air flow entering the pre-rotation channel through the air inlet forms swirling flow and flows out of the pre-rotation channel through the air outlet, and the other part of air flow entering the pre-rotation channel through the air inlet flows out of the first end of the annular body through the pneumatic hole.
According to the pre-rotation flow dividing device of the gas turbine, the flow distribution of cooling air can be controlled by controlling the air outlet of the pre-rotation channel and the throttling area of the pneumatic hole, so that the problem that the existing structure is easily affected by temperature is avoided, and the accuracy and controllability of flow distribution are improved.
In some embodiments, the pre-rotation splitting device of the gas turbine further comprises a flow blocking sleeve extending outwardly from an end face of the first end of the annular body in an axial direction of the annular body to isolate the one portion of the gas flow from the other portion of the gas flow.
In some embodiments, the pneumatic orifice is located radially outward of the flow shield cylinder along the annular body.
In some embodiments, the flow shielding cylinder comprises an inner flow shielding cylinder and an outer flow shielding cylinder, the inner flow shielding cylinder is located inside the outer flow shielding cylinder, the inner circumferential surface of the inner flow shielding cylinder is substantially flush with the end surface of the air outlet, and the pneumatic hole is located outside the outer flow shielding cylinder along the radial direction of the annular body.
In some embodiments, an end of the inner flow shield away from the annular body has a flange extending radially outward of the inner flow shield from an outer edge of the inner flow shield.
In some embodiments, the pre-rotation channel is a curved channel and a radial dimension of the pre-rotation channel gradually decreases from the outside to the inside along a radial direction of the annular body.
In some embodiments, the annular body has respective cofferdams extending outwardly from an outer periphery of the annular body in an axial direction of the annular body, and an end of each of the cofferdams remote from the annular body has a periphery extending outwardly from the outer periphery of the cofferdam in a radial direction of the cofferdam.
A gas turbine according to an embodiment of the second aspect of the present invention includes a turbine housing; a plurality of stationary vanes circumferentially disposed on an inner wall of the turbine housing; the wheel disc is arranged in the turbine shell; the movable blades are arranged on the wheel disc in a surrounding mode, and gaps are reserved between the movable blades and the stationary blades; and the pre-rotation flow dividing device is a pre-rotation flow dividing device of the gas turbine according to the embodiment of the first aspect of the invention and is positioned on the upstream side of the static blade, one part of air flow flows to the wheel disc, and the other part of air flow flows to the gap.
In some embodiments, the gas turbine further comprises a ring member, a first end of the ring member is connected to the wheel disc, the pre-rotation flow splitting device is a pre-rotation flow splitting device according to the embodiment of the first aspect of the present invention, a second end of the ring member extends into the outer shielding cylinder, and a sealing assembly is disposed between the ring member and the outer shielding cylinder.
In some embodiments, the seal assembly includes a first seal disposed on an outer wall of the ring and a second seal disposed on an inner wall of the outer flow shield cartridge.
Drawings
FIG. 1 is a schematic structural view of a pre-rotation splitting device of a gas turbine according to an embodiment of the present invention.
FIG. 2 is a cross-sectional view of a pre-rotation splitting device of a gas turbine according to an embodiment of the invention.
FIG. 3 is a partial enlarged cross-sectional view of a pre-rotation splitting device of a gas turbine according to an embodiment of the invention.
FIG. 4 is a D-D sectional view of a pre-rotation splitting device of a gas turbine according to an embodiment of the invention.
FIG. 5 is a schematic structural view of a gas turbine according to an embodiment of the present invention.
Reference numerals:
The pre-rotation flow dividing device 100, an annular body 1, a cofferdam 11, a right cofferdam 111, a left cofferdam 112, a peripheral edge 12, a right peripheral edge 121, a left peripheral edge 122, a pre-rotation channel 2, an air inlet 21, an air outlet 22, a pneumatic hole 3, a flow shielding cylinder 4, an inner flow shielding cylinder 41, an outer flow shielding cylinder 42, a wheel disc 200, a static blade 300, a movable blade 400, an annular piece 500, a sealing assembly 600, a first sealing piece 601, a second sealing piece 602 and a static piece 700.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
As shown in fig. 1 to 4, the pre-rotation splitting apparatus 100 of a gas turbine according to an embodiment of the present invention includes an annular body 1, the annular body 1 having a plurality of pre-rotation passages 2, the pre-rotation passages 2 having an air inlet 21 and an air outlet 22, and an air flow in a turbine of the gas turbine being allowed to enter the pre-rotation passages 2 through the air inlet 21 of the pre-rotation passages 2. Specifically, the plurality of pre-rotation passages 2 are uniformly spaced along the circumferential direction of the annular body 1, the air inlet 21 is located on the outer circumferential wall surface of the annular body 1, and the air outlet 22 is located on the inner circumferential wall surface of the annular body 1.
The first end (right end as viewed in fig. 2) of the annular body 1 is provided with a pneumatic orifice 3, which pneumatic orifice 3 communicates with the pre-rotation channel 2. In other words, as shown in fig. 2, the inlet of the pneumatic hole 3 communicates with the pre-rotation passage 2, and the outlet of the pneumatic hole 3 is on the right end face of the annular body 1. Further, the number of the air holes 3 is plural, and the plural air holes 3 are uniformly spaced in the circumferential direction of the annular body 1.
Thus, a part of the air flow entering the pre-spinning channel 2 through the air inlet 21 forms a swirling flow through the pre-spinning channel 2 and flows out of the pre-spinning channel 2 through the air outlet 22 and enters the annular body 1, and because in the turbine, the left side is a high pressure side, the right side is a low pressure side, and the air flow flows from the high pressure side to the low pressure side, the swirling flow in the annular body 1 flows out at the right end of the annular body 1 and flows to the wheel disc to cool the wheel disc, and the swirling flow has the same rotation direction as the wheel disc, so that the loss of rotation energy can be avoided; the other part of air entering the pre-rotation channel 2 through the air inlet 21 flows out of the pre-rotation channel 2 through the air holes 3 and flows into a gap between the movable blades and the stationary blades in the turbine, so that the root parts of the movable blades and the front section of the wheel disc can be cooled, and the gap between the movable blades and the stationary blades can be sealed to prevent high-temperature air from entering.
According to the pre-rotation flow dividing device of the gas turbine, one part of cooling air entering the pre-rotation channel forms a swirling flow through the pre-rotation channel and flows out through the air outlet, the other part flows out through the air outlet, the control of cooling air flow distribution can be realized by controlling the throttling areas of the air outlet and the air outlet, the problem that the existing structure is easily affected by temperature is avoided, and the accuracy and the controllability of flow distribution are improved.
Further, in order to improve the pre-rotation effect, an included angle is formed between the axis of the pre-rotation channel 2 and the tangent line of the inner wall surface of the annular body 1, and the included angle is in the range of 10-30 degrees. In other words, the flow direction of the air flow flowing out from the air outlet 22 of the pre-rotation passage 2 forms an angle of 10 ° to 30 ° with the tangential direction of the inner wall surface of the annular body 1. In addition, in order to further improve the cooling effect, an included angle is formed between the outlet axis of the pneumatic hole 3 and the right end face of the annular body 1, and the included angle ranges from 15 degrees to 45 degrees. In other words, the flow direction of the air flow flowing out from the air hole 3 forms an included angle of 10 ° to 30 ° with the right end surface of the annular body 1.
In some embodiments, the pre-rotation splitting apparatus 100 of the gas turbine of the present embodiment further includes a flow shielding cylinder 4, where the flow shielding cylinder 4 extends outwardly from the end surface of the first end of the annular body 1 along the axial direction of the annular body 1 to isolate one portion of the gas flow from another portion of the gas flow. In other words, as shown in fig. 2, the flow shielding cylinder 4 is coaxially disposed with the annular body 1, and the left end of the flow shielding cylinder 4 is connected with the right end of the annular body 1, and the flow shielding cylinder 4 is used for isolating a part of the air flow flowing out of the air outlet 22 and another part of the air flow flowing out of the air hole 3, so as to prevent the two parts of the air flows from interfering with each other.
In some embodiments, the pneumatic orifice 3 is located radially outside the flow-masking cylinder 4 along the annular body 1. In other words, as shown in fig. 2, since the air inlet 21 of the pre-rotation channel 2 is located on the outer peripheral surface of the annular body 1, the air outlet 22 of the pre-rotation channel 2 is located on the inner peripheral surface of the annular body 1, and the air hole 3 is provided on the right end surface of the annular body 1, in order to isolate the air flow flowing out of the air outlet 22 and the air flow flowing out of the air hole 3, the air hole 3 needs to be opened on the right end surface of the annular body 1 on the outer side of the flow shielding cylinder 4 in the radial direction thereof, so as to realize the flow direction of the two air flows.
In some embodiments, the flow shielding cylinder 4 includes an inner flow shielding cylinder 41 and an outer flow shielding cylinder 42, the inner flow shielding cylinder 41 is located inside the outer flow shielding cylinder 42, and an inner circumferential surface of the inner flow shielding cylinder 41 is substantially flush with an end surface of the air outlet 22, and the air hole 3 is located outside the outer flow shielding cylinder 42 in a radial direction of the annular body 1.
In other words, as shown in fig. 2 and 3, two flow shielding cylinders, that is, an inner flow shielding cylinder 41 and an outer flow shielding cylinder 42, are connected to the right end surface of the annular body 1, the inner flow shielding cylinder 41, the outer flow shielding cylinder 42 and the annular body 1 are all coaxially arranged, the inner flow shielding cylinder 41 is located at the inner side of the outer flow shielding cylinder 42 along the radial direction of the annular body 1, and the pneumatic hole 3 is located at the outer side of the outer flow shielding cylinder 42 along the radial direction of the annular body 1. Therefore, the two-layer flow shielding cylinder is used for isolating the two-part air flow, so that the interference of the two-part air flow can be further prevented, and the cooling and sealing effects are improved.
In some embodiments, the end of the inner flow masking cylinder 41 remote from the annular body 1 has a flange 43 extending radially outwardly of the inner flow masking cylinder 41 from the outer edge of the inner flow masking cylinder 41. In other words, as shown in fig. 2 and 3, the right end of the inner shield tube 41 has a flange 43, and the flange 43 extends radially outwardly from the outer edge of the right end of the inner shield tube 41.
In some embodiments, as shown in fig. 4, the pre-rotation channel 2 is a curved channel, and the radial dimension of the pre-rotation channel 2 gradually decreases from the outside to the inside in the radial direction of the annular body 1. It will be appreciated that the pre-swirl flow splitting device of a gas turbine according to an embodiment of the present invention can further enhance the effect of forming a swirling flow by bending the pre-swirl passage 2 whose radial dimension gradually decreases from the outside to the inside in the radial direction of the annular body 1.
In some embodiments, the annular body 1 has respective cofferdams 11 extending outwardly from the outer periphery of the annular body 1 in the axial direction of the annular body 1 at both ends, and the end of each cofferdam 11 remote from the annular body 1 has a peripheral rim 12 extending outwardly from the outer periphery of the cofferdam 11 in the radial direction of the cofferdam. In other words, as shown in fig. 2 and 3, the right end of the annular body 1 has a right cofferdam 111, the right cofferdam 111 extending rightward in the axial direction of the annular body 1 from the outer periphery of the annular body 1, the right end of the right cofferdam 111 having a right periphery 121, the right periphery 121 extending outward in the radial direction of the right cofferdam 121 from the outer periphery of the right cofferdam 111; the left end of the annular body 1 has a left cofferdam 112, the left cofferdam 112 extending from the outer periphery of the annular body 1 to the left in the axial direction of the annular body 1, the left end of the left cofferdam 112 having a left periphery 122, the left periphery 122 extending from the outer periphery of the left cofferdam 112 radially outwardly of the left cofferdam 112.
A pre-rotation splitting apparatus for a gas turbine according to an embodiment of the present invention is described below with reference to fig. 1-4.
As shown in fig. 1 to 4, a pre-rotation splitting device 100 of a gas turbine according to an embodiment of the present invention includes an annular body 1 and a flow shielding cylinder 4.
To facilitate mounting of the annular body 1 on a stationary part within a turbine of a gas turbine, the right end of the annular body 1 has a right cofferdam 111, the right cofferdam 111 extends from the outer periphery of the annular body 1 to the right in the axial direction of the annular body 1, the right end of the right cofferdam 111 has a right periphery 121, the right periphery 121 extends radially outwardly of the right cofferdam 121 from the outer periphery of the right cofferdam 111, and the right periphery 121 is connected to the stationary part within the turbine.
The left end of the annular body 1 has a left cofferdam 112, which left cofferdam 112 extends from the outer periphery of the annular body 1 to the left in the axial direction of the annular body 1, the left end of the left cofferdam 112 has a left periphery 122, which left periphery 122 extends from the outer periphery of the left cofferdam 112 radially outwardly of the left cofferdam 112, and the left periphery 122 is connected to stationary parts in the turbine.
The annular body 1 is provided with a plurality of pre-rotation channels 2, the plurality of pre-rotation channels 2 are uniformly arranged at intervals along the circumferential direction of the annular body 1, each pre-rotation channel 2 is provided with an air inlet 21 and an air outlet 22, the pre-rotation channels 2 are bent channels, and the radial dimension of the pre-rotation channels 2 gradually decreases from outside to inside along the radial direction of the annular body 1.
The right end of the annular body 1 is provided with a plurality of pneumatic holes 3, the pneumatic holes 3 are uniformly arranged at intervals along the circumferential direction of the annular body 1, and each pneumatic hole 3 is correspondingly communicated with the pre-rotation channel 2. The turbine of the gas turbine is internally provided with an air inlet 21 of the pre-rotation channel 2, a part of air flow entering the pre-rotation channel 2 forms a swirling flow and enters the annular body 1 through an air outlet 22 and flows into the wheel disc so as to cool the wheel disc; the other part flows out of the pre-rotation channel 2 through the pneumatic hole 3 and flows into a gap between the movable blade and the stationary blade in the turbine, so that the root of the movable blade and the front section of the wheel disc can be cooled, and the gap between the movable blade and the stationary blade can be sealed to prevent high-temperature gas from entering.
The flow shielding cylinder 4 is connected with the right end face of the annular body 1 and extends rightward, and is used for isolating one part of air flow flowing out of the air outlet 22 and the other part of air flow flowing out of the pneumatic hole 3, so that the two parts of air flows are prevented from interfering with each other. The number of the shielding cylinders 4 is two, and the shielding cylinders 41 and 42 are respectively an inner shielding cylinder 41 and an outer shielding cylinder 42, the inner shielding cylinder 41, the outer shielding cylinder 42 and the annular body 1 are coaxially arranged, and the inner shielding cylinder 41 is positioned on the inner side of the outer shielding cylinder 42 along the radial direction of the annular body 1.
The inner peripheral surface of the inner flow blocking cylinder 41 is substantially flush with the end surface of the air outlet 22 of the pre-swirl passage 2, and the right end of the inner flow blocking cylinder 41 has a flange 43, the flange 43 extending radially outwardly from the outer edge of the right end of the inner flow blocking cylinder 41.
The air hole 3 is located on the outer side of the outer flow blocking cylinder 42 in the radial direction of the annular body 1.
A gas turbine according to an embodiment of the present invention, which includes a turbine housing (not shown), a pre-rotation splitting device 100, a disk 200, a plurality of vanes 300, and a plurality of blades 400, is described below with reference to fig. 5.
The stator vanes 300 are circumferentially arranged on the inner wall of the turbine casing, the pre-rotation flow dividing device 100, the wheel disc 200 and the plurality of movable vanes 400 are all arranged in the turbine casing, the plurality of movable vanes 400 are circumferentially arranged on the wheel disc 200, and gaps are reserved between the movable vanes 400 and the stator vanes 300. For example, as shown in fig. 3, the center axis of the disk 200 is located at the center of the turbine housing, a plurality of blades 400 are provided at the outer periphery of the disk 200 at regular intervals, and vanes 300 are provided on the inner wall of the turbine housing on the upstream side (left side in fig. 3) of the blades 400 with a gap between the vanes 300 and the blades 400.
The pre-rotation splitting device 100 is provided on the upstream side (left side in fig. 3) of the stator blade 300, and the air flow entering the pre-rotation splitting device in the turbine radial direction is divided into two parts in the pre-rotation splitting device 100, wherein one part of the air flow flows to the wheel disc 200 to cool the wheel disc 200, and the other part of the air flow flows to the gap between the stator blade 300 and the rotor blade 400 to cool the root of the rotor blade 400 and the front section of the wheel disc 200, and also plays a role of sealing the gap to prevent invasion of high-temperature air.
Still further, as shown in FIG. 3, a stationary member 700 is further provided in the turbine housing, the right end of the stationary member 700 is connected to the stationary blade 300, and the pre-rotation split device 100 is mounted on the inner wall of the stationary member 700 and is located at the left side of the right end of the stationary member 700. Also provided within the turbine housing is an annular member 500. The right end of the ring member 500 is connected with the wheel disc 200, the left end of the ring member 500 extends into the outside flow shielding cylinder 42 of the pre-rotation flow dividing device 100, a sealing assembly 600 is arranged between the left end of the ring member 500 and the outside flow shielding cylinder 42, the sealing assembly 600 comprises a first sealing member 601 and a second sealing member 602, the first sealing member 601 is formed on the outer wall of the ring member 500, and the second sealing member 602 is arranged on the inner wall of the outside flow shielding cylinder 42.
The first sealing member 601 is a sealing tooth, specifically, a comb-shaped structure, the comb-shaped structure is formed on the outer wall of the annular member 500, the second sealing member 602 is a honeycomb structure or a wear-resistant coating, the honeycomb structure or the wear-resistant coating is arranged on the inner wall of the outer flow shielding cylinder 42, and the honeycomb structure or the wear-resistant coating is detachable so as to be replaced in time, so that flow shielding and sealing effects are ensured. Further, the present invention is not limited thereto, and the first seal 601 and the second seal 602 may be other structures for realizing sealing, respectively.
It will be appreciated that the outer wall of the portion of the ring member 500 extending into the outer shroud 42 has a comb-like structure to form the first seal 601, and the inner wall of the portion of the outer shroud 42 opposite the ring member 500 has a honeycomb structure or wear resistant coating to form the second seal 602.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.
Claims (6)
1. A gas turbine, comprising:
A turbine housing;
a plurality of stationary vanes circumferentially disposed on an inner wall of the turbine housing;
The wheel disc is arranged in the turbine shell;
The movable blades are arranged on the wheel disc in a surrounding mode, and gaps are reserved between the movable blades and the stationary blades;
A pre-rotation flow dividing device, which is located at the upstream side of the static blade, and comprises an annular body and a flow shielding cylinder, wherein the annular body is provided with a plurality of pre-rotation channels, the pre-rotation channels are provided with air inlets and air outlets, the first end of the annular body is provided with pneumatic holes communicated with the pre-rotation channels, a part of air flow entering the pre-rotation channels through the air inlets forms swirling flow and flows out of the pre-rotation channels through the air outlets, and the other part of air flow entering the pre-rotation channels through the air inlets flows out of the first end of the annular body through the pneumatic holes, and the other part of air flow flows to the wheel disc and the other part of air flow flows to the gap; the flow shielding cylinder extends outwards from the end face of the first end of the annular body along the axial direction of the annular body and is used for isolating one part of air flow from the other part of air flow, the flow shielding cylinder comprises an inner flow shielding cylinder and an outer flow shielding cylinder, the inner flow shielding cylinder is positioned on the inner side of the outer flow shielding cylinder, and the inner peripheral surface of the inner flow shielding cylinder is generally flush with the end face of the air outlet;
The first end of the annular piece is connected with the wheel disc, the second end of the annular piece stretches into the outer flow shielding cylinder, and a sealing assembly is arranged between the annular piece and the outer flow shielding cylinder; the sealing assembly comprises a first sealing piece and a second sealing piece, wherein the first sealing piece is arranged on the outer wall of the annular piece, and the second sealing piece is arranged on the inner wall of the outer side flow shielding cylinder.
2. The gas turbine of claim 1, wherein the aerodynamic bore is located radially outward of the shroud barrel along the annular body.
3. The pre-rotation splitting device of a gas turbine of claim 2, wherein the pneumatic orifice is located radially outward of the annular body from the outer shroud.
4. A gas turbine according to claim 3, wherein an end of the inner shroud remote from the annular body has a flange extending radially outwardly of the inner shroud from an outer edge of the inner shroud.
5. The gas turbine of claim 1, wherein the pre-rotation channel is a curved channel and a radial dimension of the pre-rotation channel gradually decreases from the outside to the inside along a radial direction of the annular body.
6. A gas turbine according to any one of claims 1-3, wherein the annular body has respective cofferdams extending outwardly from an outer periphery of the annular body in an axial direction of the annular body, and an end of each of the cofferdams remote from the annular body has a periphery extending outwardly from the outer periphery of the cofferdam in a radial direction of the cofferdam.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711375297.XA CN108071492B (en) | 2017-12-19 | 2017-12-19 | Gas turbine and pre-rotation flow dividing device thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711375297.XA CN108071492B (en) | 2017-12-19 | 2017-12-19 | Gas turbine and pre-rotation flow dividing device thereof |
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| Publication Number | Publication Date |
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| CN108071492A CN108071492A (en) | 2018-05-25 |
| CN108071492B true CN108071492B (en) | 2024-07-23 |
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| CN201711375297.XA Active CN108071492B (en) | 2017-12-19 | 2017-12-19 | Gas turbine and pre-rotation flow dividing device thereof |
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| CN109751130B (en) * | 2019-01-14 | 2024-09-20 | 南京航空航天大学 | Prerotation cooling system of aeroengine |
| CN111963320B (en) * | 2020-08-24 | 2021-08-24 | 浙江燃创透平机械股份有限公司 | Gas turbine interstage seal ring structure |
| CN116537895B (en) * | 2023-07-04 | 2023-09-15 | 中国航发四川燃气涡轮研究院 | Pre-rotation air supply system with comb gap control |
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| CN207795411U (en) * | 2017-12-19 | 2018-08-31 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and its part flow arrangement of prewhirling |
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| JP5134570B2 (en) * | 2009-02-23 | 2013-01-30 | 三菱重工業株式会社 | Turbine cooling structure and gas turbine |
| US8613199B2 (en) * | 2010-04-12 | 2013-12-24 | Siemens Energy, Inc. | Cooling fluid metering structure in a gas turbine engine |
| US8677766B2 (en) * | 2010-04-12 | 2014-03-25 | Siemens Energy, Inc. | Radial pre-swirl assembly and cooling fluid metering structure for a gas turbine engine |
| US9175566B2 (en) * | 2012-09-26 | 2015-11-03 | Solar Turbines Incorporated | Gas turbine engine preswirler with angled holes |
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| CN107387170B (en) * | 2017-08-14 | 2019-05-10 | 西北工业大学 | It is a kind of to be pressurized rotor disc structure for prewhirling for wheel rim sealing |
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