CN113266599B - Spindle-shaped air-entraining structure for secondary air system of gas turbine - Google Patents
Spindle-shaped air-entraining structure for secondary air system of gas turbine Download PDFInfo
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- CN113266599B CN113266599B CN202110560464.8A CN202110560464A CN113266599B CN 113266599 B CN113266599 B CN 113266599B CN 202110560464 A CN202110560464 A CN 202110560464A CN 113266599 B CN113266599 B CN 113266599B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a spindle-shaped air entraining structure for a secondary air system of a gas turbine, which comprises a two-stage rotor wheel disc, a spindle-shaped air entraining structure and an air entraining disc. The two-stage rotor wheel disc and the spindle-shaped air-entraining structure are sleeved on the air-entraining disc, an air inlet on the rotor wheel disc is over against the tip of the spindle-shaped air-entraining block, and an air-entraining hole on the spindle-shaped air-entraining structure is over against the air-entraining groove on the air-entraining disc. When the rotor disc works, the mainstream fluid enters the disc cavity area through the air inlet hole on the first-stage rotor disc along the radial direction. In the disk chamber, the gas flow is guided by a spindle-shaped gas guide block and passes through the disk chamber region via a convergent-divergent channel. And then the airflow enters the air outlet hole on the fixed disk along the radial direction, and the air outlet hole is opposite to the air guide groove on the air guide disk. The air flow turns in the flow direction in the air guide groove and is led out along the axial direction. The air entraining structure is suitable for different working conditions by selecting reasonable structural parameters. The invention has the advantages of high efficiency, low resistance, compact structure, suitability for high rotating speed and the like, and has wide market prospect.
Description
Technical Field
The invention relates to a spindle-shaped bleed air structure for a secondary air system of a gas turbine, which is used for reducing vortex of an interstage disk cavity of the gas turbine.
Background
For the cycle of the gas turbine, increasing the inlet temperature of the turbine can improve the stage operation efficiency to increase the power, but also causes the hot end part of the turbine to be subjected to higher thermal stress, which often exceeds the temperature range that the material can bear, and the research of the high-efficiency cooling technology needs to be developed urgently, so that the film cooling is one of the most effective cooling methods of the gas turbine. The low-temperature gas required for film cooling is generally extracted from the front end part, i.e. the compressor main flow, by means of bleed air devices arranged between the disks. The main flow working medium of the air compressor has high pressure, the flow direction of the main flow is often inconsistent with the flow direction of the bleed air, and a large amount of vortex can be formed when the main flow enters the bleed air device, so that higher pressure loss is caused. Therefore, a bleed structure such as a vortex reducer needs to be adopted in the bleed device, so that the pressure loss is reduced, and the bleed efficiency is improved. At present, the air entraining structures on the market and in documents are mostly tubular vortex reducers and fin vortex reducers, the air entraining structures are often complex in structure, poor in adaptability to various working conditions, more in axial space required for arrangement and poor in strength vibration performance at high rotating speed.
Disclosure of Invention
The invention aims to provide a spindle-shaped air entraining structure for a secondary air system of a gas turbine, which aims to solve the problems of large air entraining resistance, complex common air entraining structure and insufficient strength vibration performance at high rotating speed of the gas turbine.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
a spindle-shaped air-entraining structure for a secondary air system of a gas turbine comprises a first-stage rotor wheel disc, a spindle-shaped air-entraining structure, an air-entraining disc and a second-stage rotor wheel disc;
the first-stage rotor wheel disc, the spindle-shaped drainage structure and the second-stage rotor wheel disc are sequentially and integrally sleeved on the air entraining disc, and the air entraining disc is sleeved on the rotating shaft.
The invention has the further improvement that the first-stage rotor wheel disc is provided with a first-stage rotor wheel groove in the circumferential direction, 8-12 air guide holes are uniformly formed in the circumferential direction, and the aperture is 4-6 mm.
The invention has the further improvement that the spindle-shaped air entraining structure comprises a fixed disk, a plurality of spindle-shaped air entraining blocks which are uniformly arranged on the fixed disk in the circumferential direction, and air outlet holes which are uniformly arranged on the fixed disk in the circumferential direction, wherein each air outlet hole is positioned between two adjacent spindle-shaped air entraining blocks.
The invention has the further improvement that the number of the spindle-shaped air guide blocks is equal to that of the air guide holes, when air is radially fed, the tips of the spindle-shaped air guide blocks are over against the centers of the air guide holes, and if an air inlet angle exists, the staggered angle between the tips of the spindle-shaped air guide blocks and the centers of the air guide holes is not more than 5 degrees.
The invention has the further improvement that a plurality of air guide grooves are uniformly arranged on the air guide disc along the axial direction in the circumferential direction, and the air guide grooves are opposite to the center of the air outlet hole.
The invention has the further improvement that one end of the air-entraining groove is closed along the axial direction, and the other end is open, the depth of the air-entraining groove is 4-8mm, the width of the air-entraining groove is 4-8mm, and the number of the air-entraining grooves is equal to the number of the air outlet holes.
The invention is further improved in that the radius of the top end of the spindle-shaped air guide block is not less than 1/2 of the radial depth of the disc cavity and not more than 4/5 of the radial depth of the disc cavity, the axial section of the spindle-shaped air guide block is formed by two Bessel curves, and the top end of the air guide block is rounded.
The invention is further improved in that the aperture of the air outlet holes is 4-8mm, and the number of the air outlet holes is equal to the number of the air guide holes.
The invention is further improved in that the second-stage rotor wheel disc is circumferentially engraved with second-stage rotor wheel grooves.
Compared with the prior art, the invention has the following advantages:
the invention provides a spindle-shaped air entraining structure for a secondary air system of a gas turbine, which reasonably plans the through-flow structure of the secondary air entraining, can better organize the flow of the entrained air, limits the formation of vortexes after the entrained air enters a disc cavity area, and reduces the flow resistance. The air entraining structure is reasonably designed in assembly and fixed arrangement, the axial space required by arrangement of the air entraining structure is shortened, and the air entraining structure has better strength vibration performance at high rotating speed and improves the operation safety.
Furthermore, bleed air enters the disc cavity along the bleed air holes, and eddy flow can be formed because high-speed jet flow enters a large space, so that the spindle-shaped bleed air block is adopted to limit the flow space of the bleed air entering the disc cavity, the radial air flow channel is a gradually-reducing-gradually-expanding channel, the formation of flow separation is limited, and the flow resistance is reduced. And the Bezier curve design is adopted, so that the flow line is smoother, and the flow form is more stable.
Furthermore, the bleed air has a higher speed along the circumferential direction when entering the bleed holes, the spindle-shaped bleed air blocks limit the circumferential speed development, guide the airflow to flow along the radial direction, and limit the formation of circumferential vortex.
Furthermore, a compact arrangement method is adopted, the air entraining structures can be arranged in a shorter axial interval, and the axial space occupied by the two-stage rotor wheel disc and the air entraining structures is shortened.
Furthermore, the spindle-shaped air entraining blocks are integrally welded on the fixed disk, and under the action of high-rotating-speed centrifugal force, the spindle-shaped air entraining blocks are subjected to radial tensile stress, so that higher centrifugal force load can be borne.
Furthermore, the spindle-shaped air entraining block adopts a hollow design, so that the weight of the air entraining block can be reduced, the centrifugal force generated during high-speed rotation is further reduced, and the safety of the air entraining block during high-speed rotation is ensured.
Furthermore, the shape and number of the spindle-shaped air-entraining blocks, the size and the opening direction of the air-entraining holes, the depth of the air-entraining grooves and the like can be changed according to actual conditions so as to adapt to different working conditions.
In conclusion, the spindle-shaped air entraining structure for the secondary air system of the gas turbine can obviously reduce the eddy current during air entraining, reduce the flow resistance, reduce the required axial space through reasonable arrangement, and improve the safety and stability of the air entraining structure under high-rotating-speed operation.
Drawings
Fig. 1 is an exploded view of the overall structure of a spindle-shaped bleed air structure for a secondary air system of a gas turbine according to the present invention.
FIG. 2 is a schematic assembly view of a spindle-shaped bleed air structure for a secondary air system of a gas turbine according to the present invention.
FIG. 3 is a schematic illustration of a first stage rotor disk of the present invention.
FIG. 4 is a schematic illustration of a second stage rotor disk of the present invention.
Fig. 5 is a partial enlarged view of the spindle-shaped drainage structure of the present invention.
FIG. 6 is a schematic diagram of the spindle-shaped air-entraining block of the present invention in different forms, including a symmetrical flow-guiding block structure and an asymmetrical flow-guiding block structure.
Fig. 7 is a partial enlarged view of the gas induction tray of the present invention.
Description of reference numerals:
the first-stage rotor wheel disc mainly comprises 1, 2 and 10, wherein 1 is the first-stage rotor wheel disc, 2 is a first-stage rotor wheel groove, and 10 is an air guide hole;
the second-stage rotor disk mainly comprises 6 and 7, wherein 6 is the second-stage rotor disk, and 7 is a second-stage rotor wheel groove;
the spindle-shaped drainage structure mainly comprises 4, 5 and 8, wherein 4 is a spindle-shaped air guide block, 5 is a fixed disc, and 8 is an air outlet;
the air guide disc mainly comprises 3 and 9, wherein 3 is the air guide disc, and 9 is the air guide groove.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings. It should not be understood that the scope of the above-described subject matter of the present invention is limited to the following. Various substitutions and alterations according to the knowledge and routine of those skilled in the art are intended to be included within the scope of the present invention without departing from the spirit and scope of the present invention as defined by the appended claims.
Referring to fig. 1 to 6, the spindle-shaped bleed air structure for a secondary air system of a gas turbine provided by the invention comprises a first-stage rotor disc 1, a spindle-shaped bleed air structure, a bleed air disc and a second-stage rotor disc 7. A first-stage rotor wheel disc 1 is engraved with a first-stage rotor wheel groove 2, 8-12 air-entraining holes 10 are uniformly arranged along the circumferential direction, and the aperture is 4-6 mm; the spindle-shaped air-entraining structure mainly comprises a spindle-shaped air-entraining block 4, a fixed disk 5 and an air outlet 8. The number of the spindle-shaped air guide blocks 4 is equal to that of the air guide holes 10, the spindle-shaped air guide blocks are uniformly fixed on the air guide disc 3 along the circumferential direction, the tips of the spindle-shaped air guide blocks 4 are ensured to be over against the center of the air guide holes 10 during assembly (when air enters in the radial direction), if an air inlet angle exists, the positions of the angular tips of the spindle-shaped air guide blocks 4 can be correspondingly adjusted according to the form of a flow field, and the staggered angle is not more than 5 degrees. The shape of the spindle-shaped bleed air block 4 is generally an axisymmetric structure, and can also be changed into an asymmetric structure according to actual operation conditions such as rotating speed and the like, including but not limited to a flow-shaped structure such as a wing-shaped structure, a wing-shaped structure and the like. The radius of the top end of the spindle-shaped air entraining block 4 is not less than 1/2 of the radial depth of the disc cavity and not more than 4/5 of the radial depth of the disc cavity. The axial section of the spindle-shaped air entraining block 4 consists of two Bezier curves, and the top end of the air entraining block can be rounded according to actual conditions. When the rotating speed is too high (more than 10000 rpm), the spindle-shaped air-entraining block 4 can be processed by a cavitation-resistant material such as titanium alloy, nickel-chromium alloy and the like, and surface strengthening treatment can be carried out by means of thermal spraying, brazing stellite alloy, high-frequency quenching and the like.
An air outlet 8 is arranged between two adjacent spindle-shaped air-entraining blocks 4 on the air-entraining disc 3. The air guide plate 3 is uniformly provided with a plurality of air guide grooves 9 along the axial direction in the circumferential direction, one end of each air guide groove 9 is closed along the axial direction, the other end of each air guide groove 9 is open, the depth of each air guide groove is 4-8mm, the width of each air guide groove is 4-8mm, the number of the air guide grooves is equal to that of the air outlet holes 8, the air guide grooves 9 are ensured to be over against the centers of the air outlet holes 8 during assembly, and the air guide plate 3 is directly sleeved on the rotating shaft. And a second-stage rotor wheel groove 7 is carved on the second-stage rotor wheel disc 6 in the circumferential direction. In the assembly relation, a compact combined design mode is adopted, the spindle-shaped air guide block and the wheel disc structure are combined and assembled, the disassembly and the assembly are convenient to replace, the practical application is more flexible, and the spindle-shaped air guide block structure can be replaced according to different design working condition parameters. The first-stage rotor disk 1, the spindle-shaped drainage structure and the second-stage rotor disk 6 are sequentially and integrally sleeved on the air guiding disk, and the structure is more compact. The two-stage rotor wheel disc, the spindle-shaped air entraining structure, the air entraining disc and the rotating shaft rotate integrally, and all parts do not rotate relatively.
The working principle of the invention is as follows: under the working state, the first-stage rotor disk 1, the spindle-shaped air entraining structure and the second-stage rotor disk 6 are sequentially sleeved on the air entraining disk 3. The tip of the spindle-shaped air-entraining block 4 is opposite to the center of an air-entraining hole 10 on the rotor wheel disc, and an air outlet hole 8 on the spindle-shaped air-entraining structure is opposite to an air-entraining groove 9 on the air-entraining disc 3. The air guide disc 3 is sleeved on the rotating shaft, and when the air guide disc is in operation, the two-stage rotor disc, the spindle-shaped air guide structure, the air guide disc 3 and the rotating shaft rotate integrally, and all parts do not rotate relatively. Two stages of compressor blades are respectively arranged on a first-stage rotor wheel groove 2 on the first-stage rotor wheel disc 1 and a second-stage rotor wheel groove 7 on the second-stage rotor wheel disc 7, and a main flow area of the compressor is arranged between the two stages of compressor blades. When the rotor disc is in work, the main flow of the compressor enters the disc cavity area through the air guide holes 10 on the wheel hubs of the two-stage rotor disc in the radial direction under the action of pressure difference. The fluid from each bleed orifice 10 is divided in the disc chamber by the tip of the spindle-shaped bleed block 4 opposite it into two streams, each of which merges with the stream from its adjacent bleed orifice 10. The airflow flows centripetally along the radial direction and is guided by the spindle-shaped drainage structure to pass through a gradually reducing-gradually expanding channel. After passing through the disc cavity area, the air flow enters the air outlet hole 8 on the fixed disc along the radial direction, and the air outlet hole 8 is over against the air guiding groove 9 on the air guiding disc. The air flow turns in the flow direction in the air guide groove 9 and is led out along the axial direction so as to be used for cooling the air film of the subsequent hot end component.
Although the invention has been described in detail with respect to the general description and the specific embodiments thereof, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (7)
1. A spindle-shaped air-entraining structure for a secondary air system of a gas turbine is characterized by comprising a first-stage rotor disc (1), a spindle-shaped flow-guiding structure, an air-entraining disc (3) and a second-stage rotor disc (6);
wherein, the first-stage rotor wheel disc (1), the spindle-shaped drainage structure and the second-stage rotor wheel disc (6) are sequentially and integrally sleeved on the air guide disc (3), and the air guide disc (3) is sleeved on the rotating shaft;
a first-stage rotor wheel groove (2) is formed in the circumferential direction of the first-stage rotor wheel disc (1), 8-12 air guide holes (10) are uniformly formed in the circumferential direction, and the aperture is 4-6 mm;
fusiform drainage structure includes fixed disk (5), and a plurality of fusiform air guide block (4) of circumference even setting on fixed disk (5) to and air outlet (8) on fixed disk (5) are evenly seted up to circumference, and every air outlet (8) are located between two adjacent fusiform air guide block (4).
2. The spindle-shaped air-entraining structure for the secondary air system of the gas turbine as claimed in claim 1, characterized in that the number of the spindle-shaped air-entraining blocks (4) is equal to that of the air-entraining holes (10), when the air is introduced radially, the tip of the spindle-shaped air-entraining block (4) is opposite to the center of the air-entraining hole (10), and if there is an air-intake angle, the offset angle between the tip of the spindle-shaped air-entraining block (4) and the center of the air-entraining hole (10) is not more than 5 °.
3. The spindle-shaped air-entraining structure for the secondary air system of the gas turbine as claimed in claim 1, characterized in that the air-entraining disk (3) is provided with a plurality of air-entraining grooves (9) uniformly along the axial direction in the circumferential direction, and the air-entraining grooves (9) are aligned with the centers of the air outlet holes (8).
4. The spindle-shaped air-entraining structure for the secondary air system of a gas turbine as claimed in claim 3, characterized in that the air-entraining grooves (9) are closed at one end and open at the other end in the axial direction, and are 4-8mm deep and 4-8mm wide, the number of which is equal to the number of the air outlet holes (8).
5. The spindle-shaped air-entraining structure for a secondary air system of a gas turbine as claimed in claim 1, characterized in that the radius of the tip of the spindle-shaped air-entraining block (4) is not less than 1/2 and not more than 4/5 of the radial depth of the disk cavity, the axial section of the spindle-shaped air-entraining block (4) is formed by two Bezier curves, and the tip of the air-entraining block is rounded.
6. Spindle-shaped bleed air structure for a secondary air system of a gas turbine according to claim 1, characterised in that the aperture of the outlet openings (8) is between 4 and 8mm, the number of outlet openings (8) being equal to the number of bleed air openings (10).
7. Spindle-shaped air-entraining structure for a secondary air system of a gas turbine according to claim 1, characterised in that the second-stage rotor disk (6) is engraved with second-stage rotor grooves (7) in the circumferential direction.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110560464.8A CN113266599B (en) | 2021-05-21 | 2021-05-21 | Spindle-shaped air-entraining structure for secondary air system of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110560464.8A CN113266599B (en) | 2021-05-21 | 2021-05-21 | Spindle-shaped air-entraining structure for secondary air system of gas turbine |
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| CN113266599A CN113266599A (en) | 2021-08-17 |
| CN113266599B true CN113266599B (en) | 2022-08-09 |
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| CN112648077A (en) * | 2020-12-17 | 2021-04-13 | 北京航空航天大学 | Novel nozzle fin combined type vortex reducing system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE10159670A1 (en) * | 2001-12-05 | 2003-06-18 | Rolls Royce Deutschland | Vortex rectifier in the high pressure compressor of a gas turbine |
| DE102008024146A1 (en) * | 2008-05-19 | 2009-11-26 | Rolls-Royce Deutschland Ltd & Co Kg | Combined vortex rectifier |
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2021
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103867235A (en) * | 2012-12-18 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Tubular vortex reducer air inducing system |
| CN104675440A (en) * | 2015-03-03 | 2015-06-03 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Cooling air guide structure of turbine rotor of gas turbine |
| CN107060889A (en) * | 2017-04-19 | 2017-08-18 | 西北工业大学 | A kind of double disc turbine disks with disk chamber turbulence columns |
| CN209483712U (en) * | 2018-11-27 | 2019-10-11 | 南京航空航天大学 | A kind of compressor goes rotation to subtract vortex structure |
| CN110081027A (en) * | 2019-04-29 | 2019-08-02 | 南京航空航天大学 | It is a kind of to subtract whirlpool device bleed air system for the finned of compressor |
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