CN114909188B - Sealing structure for rim of turbine disc of gas turbine - Google Patents
Sealing structure for rim of turbine disc of gas turbine Download PDFInfo
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- CN114909188B CN114909188B CN202210521593.0A CN202210521593A CN114909188B CN 114909188 B CN114909188 B CN 114909188B CN 202210521593 A CN202210521593 A CN 202210521593A CN 114909188 B CN114909188 B CN 114909188B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
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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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- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application discloses gas turbine wheel rim structure of obturating belongs to the technical field of turbine disk stage-to-stage obturating, and it includes quiet dish of turbine, turbine carousel, the quiet dish of turbine with be provided with the clearance between the turbine carousel, the quiet dish of turbine with install the holding ring between the turbine carousel, be provided with the tesla valve passageway in the holding ring, the air inlet of tesla valve passageway with the inside wall of holding ring is linked together, the gas outlet of tesla valve passageway with the lateral wall of holding ring is linked together. This application has the emergence of effectively preventing the gas invasion, reduces the effect that lets in the cold air volume of obturating in dish chamber.
Description
Technical Field
The application relates to the technical field of sealing between turbine disc stages, in particular to a sealing structure of a gas turbine disc rim.
Background
The most effective way to improve the performance of an aircraft gas turbine engine is to increase the turbine inlet gas temperature, since the turbine is subjected to high thermal stress and centrifugal stress when operating at high temperature and high speed for a long time, and in order to ensure the reliable operation of the engine, the turbine blade air system is required to provide turbine blade cooling air, thereby reducing the turbine blade temperature.
After the cool air provided by the air system of the aircraft engine reaches the static disc from the internal channel, part of the cool air is used for preventing high-temperature main flow gas from entering the cavity of the rotary disc, and the part of the cool air is generally called sealing cool air. In the related art, the aero-engine generally uses a labyrinth structure as a rim seal, and the seal cold air prevents mainstream high-temperature fuel gas from entering a rotary disk cavity through a labyrinth mechanism. The phenomenon that the main flow gas enters the disc cavity through the sealing of the wheel rim is called gas invasion or gas backflow.
Aiming at the related technologies, the inventor considers that the amount of the sealed cold air is difficult to control, if the sealed cold air is insufficient, mainstream high-temperature gas enters the engine through the flange sealing structure, a gas invasion phenomenon is generated, and the service life of the engine is greatly reduced; however, if the amount of the introduced cold air is too large, the flow loss of the engine is increased, and the efficiency is lowered.
Disclosure of Invention
In order to more effectively prevent the emergence of gas invasion, reduce the sealed severe cold tolerance that lets in the dish chamber, the application provides a structure of obturating of gas turbine wheel rim.
The application provides a gas turbine dish rim structure of obturating adopts following technical scheme:
the utility model provides a structure of obturating of gas turbine wheel rim, includes the quiet dish of turbine, turbine carousel, the quiet dish of turbine with be provided with the clearance between the turbine carousel, the quiet dish of turbine with install the holding ring between the turbine carousel, be provided with the tesla valve passageway in the holding ring, the air inlet of tesla valve passageway with the inside wall of holding ring is linked together, the gas outlet of tesla valve passageway with the lateral wall of holding ring is linked together.
By adopting the technical scheme, the sealed cold air entering the turbine disc cavity enters the Tesla valve channel through the air inlet of the Tesla valve channel, the sealed cold air in the Tesla valve channel flows into the gap between the turbine static disc and the turbine rotary disc through the air outlet of the Tesla valve channel, then the sealed cold air flows into main stream gas from the gap, and the sealed cold air can prevent high-temperature gas from invading the turbine disc cavity through the gap; when the mainstream gas gets into tesla valve passageway through the clearance of the carousel of turbine quiet dish and turbine in, because the outstanding one-way performance that switches on of tesla valve passageway, the high temperature gas that gets into in the tesla valve passageway from the gas outlet hardly gets into the dish intracavity through the air inlet, the appearance that the gas invasion can more effectively be prevented in setting up of tesla valve passageway to can suitably reduce and seal tight cold gas volume, utilize the reliable effect of obturating of the volume assurance of less obturating cold gas, and then improve turbine start efficiency.
Preferably, the positioning ring comprises a first ring body fixedly connected to the turbine stationary disc and a second ring body fixedly connected to the turbine rotary disc, first annular grooves are formed in the side face, close to the second ring body, of the first ring body at intervals, second annular grooves are formed in the side face, close to the first ring body, of the second ring body at intervals, the first annular grooves and the second annular grooves are arranged in a staggered mode, and the tesla valve channel is formed by combining the first annular grooves and the second annular grooves.
Through adopting above-mentioned technical scheme, when the high temperature gas got into the locating ring through the clearance between turbine quiet dish and the turbine carousel in, the high temperature gas passed through first ring channel and second ring channel in proper order, the inside wall of first ring channel makes the high temperature gas that gets into in the first ring channel flow direction that deflects, the high temperature gas in the first ring channel of outflow strikes with the gas that gets into in the locating ring channel, thereby it gets into the dish chamber through the locating ring to block the high temperature gas, and in the same way, being provided with of second ring channel does benefit to and hinders the high temperature gas and flow.
Preferably, in the holding ring tesla valve passageway is provided with a plurality ofly, and is a plurality of tesla valve passageway winds the axis of the quiet dish of turbine is evenly arranged, holding ring fixed connection in on the quiet dish of turbine, offer on the inside wall of holding ring be used for with the air inlet ring groove that tesla valve passageway air inlet is linked together, the spaced apart air outlet groove that is equipped with on the outer peripheral face of holding ring, air outlet groove with the gas outlet one-to-one of tesla valve passageway.
Through adopting above-mentioned technical scheme, being provided with of air inlet ring groove does benefit to in the high-efficient leading-in air inlet of the air conditioning of obturating that will get into the clearance between turbine quiet dish and the turbine carousel, and the setting of going out the air groove can reduce on the one hand high temperature gas and get into in the tesla valve passageway, on the other hand the setting of going out the air groove makes in the high temperature gas can only concentrate gets into tesla valve passageway from going out the air groove to improve the shutoff effect of the air conditioning of obturating.
Preferably, the positioning ring is fixedly connected to the side surface of the turbine static disc close to the turbine rotary disc, a plurality of circulating pipes penetrate through the positioning ring, the inner side walls of two sides of each circulating pipe are respectively communicated with a shunting ring pipe, the shunting ring pipes are arranged in a staggered mode along the length direction of the circulating pipes, and the tesla valve passage is formed by combining a plurality of the circulating pipes.
Through adopting above-mentioned technical scheme, directly utilize runner pipe and reposition of redundant personnel ring canal as the passageway that high temperature gas and seal up the air conditioning flow, be favorable to reducing the influence of gas and air conditioning to the holding ring to improve the life of holding ring, when high temperature gas passes through the gas outlet and gets into in the runner pipe, the setting up of reposition of redundant personnel ring canal makes the air current of dispersion strike each other, and then be favorable to blockking that high temperature gas continues to move along the runner pipe, improve the effect that Tesla valve passageway blockked high temperature gas.
Preferably, the holding ring include fixed connection in ring one on the turbine quiet dish and set up in ring two on the ring one, ring one with be provided with the connecting plate between the ring two, ring one with a plurality of water conservancy diversion annuli have all been seted up on the side that ring two are close to each other, just ring one on the water conservancy diversion annular with on the ring two the water conservancy diversion annular about the connecting plate symmetrical arrangement, tesla valve passageway comprises the water conservancy diversion annular.
Through adopting above-mentioned technical scheme, the setting of connecting plate can be strengthened ring body one and the ring body two between be connected, when high-temperature gas got into the clearance between ring body one and the ring body two, high-temperature gas is shunted by the water conservancy diversion annular, and the water conservancy diversion annular of symmetrical arrangement makes the high-temperature gas of two strands of shunts can impact a department of mainstream high-temperature gas simultaneously, and then improves the separation effect of tesla valve passageway to high-temperature gas.
Preferably, a plurality of reposition of redundant personnel ring bodies of fixedly connected with on the connecting plate, reposition of redundant personnel ring body with water conservancy diversion annular one-to-one, reposition of redundant personnel ring body set up in the water conservancy diversion annular, just the surface of reposition of redundant personnel ring body with corresponding interval between the inside wall of water conservancy diversion annular is certain, reposition of redundant personnel ring body is close to spaced apart being equipped with the arc wall on the side of the gas outlet of tesla valve passageway.
Through adopting above-mentioned technical scheme, being provided with of reposition of redundant personnel ring body does benefit to the reposition of redundant personnel efficiency that improves high temperature gas, and the setting up of separation ring body makes the high temperature gas that gets into the water conservancy diversion annular hug closely the inside wall flow of water conservancy diversion annular to make the gas of reposition of redundant personnel concentrate more when flowing out the water conservancy diversion annular, and then improve the separation effect to mainstream high temperature gas, the setting of arc wall is favorable to making the gas of reposition of redundant personnel produce less vortex, thereby reduces the speed of reposition of redundant personnel gas.
Preferably, the connecting plate is fixedly connected with a flow dividing member, the flow dividing member comprises a first flow dividing plate and a second flow dividing plate, the first flow dividing plate and the second flow dividing plate are arranged between the first ring body and the second ring body, the end parts, far away from each other, of the first flow dividing plate are in a blade shape, and the end parts, far away from the channel air outlet of the tesla valve, of the first flow dividing plate are in an arc shape.
By adopting the technical scheme, when high-temperature fuel gas enters the Tesla valve channel through the gas outlet, the blade-shaped end part of the first splitter plate enables the high-temperature fuel gas to be split in advance, and the arc-shaped end part of the first splitter plate enables the split high-temperature fuel gas to impact each other, so that the speed of the high-temperature fuel gas is reduced; when the sealed cold air enters the Tesla valve channel through the air inlet, the blade-shaped end part of the second diversion plate enables the sealed cold air to be diverted, and the two sealed cold air correspond to the two high-temperature fuel gases, so that the flow of the high-temperature fuel gases is blocked.
Preferably, the turbine static disc and the turbine rotary disc are both fixedly connected with sealing rings, and the sealing rings are arranged in a staggered mode.
Through adopting above-mentioned technical scheme, the setting of the ring of obturating does benefit to and prevents that high temperature gas from directly getting into the clearance between turbine carousel and the turbine quiet dish, and the setting of the ring of obturating can reduce high temperature gas and get into content and the speed in clearance.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the sealed cold air entering the turbine disc cavity enters the Tesla valve channel through an air inlet of the Tesla valve channel, the sealed cold air in the Tesla valve channel flows into a gap between the turbine static disc and the turbine rotary disc through an air outlet of the Tesla valve channel, and then the sealed cold air flows into main flow gas from the gap, and the sealed cold air can prevent high-temperature gas from invading the turbine disc cavity through the gap; when main stream gas enters a Tesla valve channel through a gap between a turbine static disc and a turbine rotating disc, high-temperature gas entering the Tesla valve channel from an air outlet is difficult to enter a disc cavity through an air inlet due to the excellent one-way conduction performance of the Tesla valve channel, and the Tesla valve channel can effectively prevent gas invasion, so that the amount of sealed cold air can be properly reduced, a reliable sealing effect is ensured by using smaller amount of sealed cold air, and the starting efficiency of the turbine is improved;
2. when high-temperature gas enters the positioning ring through a gap between the turbine static disc and the turbine rotary disc, the high-temperature gas sequentially passes through the first annular groove and the second annular groove, the inner side wall of the first annular groove enables the high-temperature gas entering the first annular groove to deflect the flowing direction, the high-temperature gas flowing out of the first annular groove impacts with the gas entering the positioning ring, and therefore the high-temperature gas is prevented from entering the disc cavity through the positioning ring;
3. when high-temperature fuel gas enters the Tesla valve channel through the gas outlet, the blade-shaped end part of the first splitter plate enables the high-temperature fuel gas to be split in advance, and the arc-shaped end part of the first splitter plate enables the split high-temperature fuel gas to impact each other, so that the speed of the high-temperature fuel gas is reduced; when the sealed cold air enters the Tesla valve channel through the air inlet, the blade-shaped end part of the second diversion plate enables the sealed cold air to be diverted, and the two sealed cold air correspond to the two high-temperature fuel gases, so that the flow of the high-temperature fuel gases is blocked.
Drawings
FIG. 1 is a schematic structural diagram of a sealing structure of a rim of a turbine disk of a gas turbine according to an embodiment of the present application.
Fig. 2 is an internal structure schematic diagram of a sealing structure of a gas turbine disk rim according to embodiment 1 of the present application.
Fig. 3 is an internal structure schematic diagram of a sealing structure of a turbine disk rim of a gas turbine according to embodiment 2 of the present application.
Fig. 4 is an internal structure schematic diagram of a sealing structure of a gas turbine disk rim according to embodiment 3 of the present application.
Fig. 5 is an internal structural schematic view of a gas turbine disk rim sealing structure according to embodiment 4 of the present application.
Fig. 6 is an enlarged schematic view at a in fig. 5.
Description of reference numerals:
1. a turbine stationary disk; 2. a turbine rotor disk; 3. a positioning ring; 31. a first ring body; 32. a second ring body; 33. a first annular groove; 34. a second annular groove; 35. an air inlet ring groove; 36. an air outlet groove; 4. a Tesla valve channel; 5. a sealing ring; 6. a flow-through tube; 61. a shunt loop pipe; 71. a ring body I; 72. a second ring body; 73. a flow guide ring groove; 74. a connecting plate; 75. a splitter ring body; 751. an arc-shaped slot; 8. a flow divider; 81. a first splitter plate; 82. a second shunting plate.
Detailed Description
The present application is described in further detail below with reference to figures 1-5.
The embodiment of the application discloses gas turbine dish rim structure of obturating.
Example 1
Referring to fig. 1 and 2, the sealing structure of the turbine disk rim of the gas turbine comprises a turbine static disk 1, a turbine rotary disk 2, a positioning ring 3 and a tesla valve channel 4.
Referring to fig. 2, a gap exists between the turbine static disc 1 and the turbine rotary disc 2, the edges of the turbine static disc 1 and the turbine rotary disc 2 are both provided with a sealing ring 5, and the axis of the sealing ring 5 coincides with the axis of the turbine static disc 1. The sealing rings 5 of the turbine static disc 1 are arranged in two, the sealing rings 5 on the turbine rotary disc 2 are arranged in two, and the sealing rings 5 on the turbine static disc 1 and the sealing rings 5 on the turbine rotary disc 2 are arranged in a staggered mode. The setting of the ring 5 of obturating can prevent most high temperature gas from getting into the clearance between the turbine static disc 1 and the turbine, disc 2 on the one hand to reduce the possibility that the gas invasion takes place, and the setting of the ring 5 of obturating can reduce the velocity of flow of the high temperature gas that gets into the clearance on the other hand.
Referring to fig. 2, the positioning ring 3 is disposed in the gap between the turbine stationary disk 1 and the turbine rotary disk 2, the positioning ring 3 includes a first ring 31 and a second ring 32, the first ring 31 is fixedly connected to the side of the turbine stationary disk 1 close to the turbine rotary disk 2, and the axis of the first ring 31 coincides with the axis of the turbine stationary disk 1. The second ring body 32 is fixedly connected to the side surface of the turbine rotary disk 2 close to the turbine static disk 1, and the axis of the second ring body 32 coincides with the axis of the first ring body 31.
Referring to fig. 2, a plurality of first annular grooves 33 are formed in a side surface of the first ring body 31 close to the second ring body 32, the plurality of first annular grooves 33 are arranged at intervals, and an axis of the first annular groove 33 coincides with an axis of the first ring body 31. The side surface of the second ring body 32 close to the first ring body 31 is provided with a plurality of second annular grooves 34, the plurality of second annular grooves 34 are arranged at intervals, the axis of the second annular grooves 34 coincides with the axis of the second ring body 32, and the first annular grooves 33 and the second annular grooves 34 are arranged in a staggered manner. The tesla valve channel 4 is formed by combining a first annular groove 33 and a second annular groove 34, the air inlet of the tesla valve channel 4 is communicated with the inner side wall of the positioning ring 3, the air outlet of the tesla valve channel 4 is communicated with the outer peripheral surface of the positioning ring 3, and the air inlet and the air outlet of the tesla valve channel 4 are communicated with the gap.
Referring to fig. 2, a part of high-temperature fuel gas enters the gap through the sealing ring 5, when the high-temperature fuel gas enters the tesla valve channel 4 through the gas outlet on the positioning ring 3, the arrangement of the first annular groove 33 and the second annular groove 34 enables the high-temperature fuel gas to be divided, and the inner side walls of the first annular groove 33 and the second annular groove 34 enable the divided fuel gas to impact the main fuel gas, so that the flow of the high-temperature fuel gas in the tesla valve channel 4 is blocked; after the cold air enters the disc cavity, part of the cold air cools the turbine blades through the passages in the turbine static disc 1 and the turbine rotating disc 2, and the other part of the cold air enters the tesla valve passage 4 through the air inlet on the positioning ring 3, so that the cold air in the positioning ring 3 is condensed by the tesla valve passage 4, and the gas penetrating into the sealing ring 5 is further prevented from entering the disc cavity through the tesla valve passage 4. The performance that tesla valve passageway 4 one-way conduction can effectively hinder the flow of high temperature gas, in the prerequisite of guaranteeing that the high temperature gas does not get into the dish chamber, operating personnel can suitably reduce and seal tight cold tolerance to utilize the volume of less air conditioning of sealing to guarantee reliable effect of sealing, and then improve turbine start efficiency.
Example 2
Referring to fig. 3, the difference from embodiment 1 is a positioning ring 3 and a tesla valve passage 4. In the embodiment 2, the positioning ring 3 is in a circular ring shape, and the positioning ring 3 is fixedly connected to the side surface of the turbine static disc 1 close to the turbine rotary disc 2. The tesla valve passages 4 in the positioning ring 3 are provided in plural, and the plural tesla valve passages 4 are uniformly arranged around the axis of the positioning ring 3. An air inlet ring groove 35 is formed in the inner side wall of the positioning ring 3, and the air inlet ring groove 35 is communicated with an air inlet of the Tesla valve channel 4. A plurality of air outlet grooves 36 are arranged on the peripheral surface of the positioning ring 3 at intervals, the air outlet grooves 36 correspond to the air outlets of the Tesla valve channels 4 one by one, and the air outlet grooves 36 are communicated with the air outlets of the Tesla valve channels 4.
Referring to fig. 3, the arrangement of the gas outlet groove 36 can reduce the high-temperature gas from entering the tesla valve channel 4 on the one hand, and the arrangement of the gas outlet groove 36 can concentrate the position of the high-temperature gas entering the tesla valve channel 4 on the other hand; the provision of the air inlet ring groove 35 facilitates the introduction of sealed cold air into the air inlet of the tesla valve passage 4, the tesla valve passage 4 enabling the cold air to condense, the cold air entering the tesla valve passage 4 from the air inlet of the positioning ring 3, thereby preventing the gas from entering the disc cavity through the tesla valve passage 4. The arrangement of the tesla valve passage 4 is advantageous for reducing the amount of sealed cold air, thereby improving engine performance.
Example 3
Referring to fig. 4, the difference from embodiment 1 is a positioning ring 3 and a tesla valve passage 4. The locating ring 3 is the ring form, and locating ring 3 fixed connection is in the side that the quiet dish of turbine 1 is close to turbine carousel 2, and the axis of locating ring 3 and the dead dish of turbine 1's axis coincidence. A plurality of circulating pipes 6 are arranged in the positioning ring 3 in a penetrating mode, one end of each circulating pipe 6 extends to the inner side wall of the positioning ring 3, and the other end of each circulating pipe 6 extends to the outer peripheral face of the positioning ring 3. Two side surfaces of the circulating pipe 6, which are close to the turbine static disc 1 and the turbine rotary disc 2, are both communicated with a circulating pipe 61, and the circulating pipes 61 are arranged in a staggered mode along the length direction of the circulating pipe 6. The tesla valve passage 4 is formed by combining a plurality of flow pipes 6, and the plurality of flow pipes 6 are arranged side by side.
Referring to fig. 4, the circulation pipe 6 and the distribution loop 61 are directly used as a passage for high temperature gas and sealed cold gas to flow, which is beneficial to reducing the influence of the gas and the cold gas on the positioning ring 3, thereby improving the service life of the positioning ring 3. When high-temperature gas enters the circulating pipe 6 through the gas outlet, the dispersed gas flows impact each other due to the arrangement of the flow dividing ring pipe 61, so that the high-temperature gas is prevented from moving along the circulating pipe 6, and the effect of preventing the high-temperature gas from flowing through the Tesla valve passage 4 is improved due to the arrangement of the flow dividing ring pipe 61.
Example 4
Referring to fig. 5 and 6, the difference from embodiment 1 is a positioning ring 3 and a tesla valve passage 4. The positioning ring 3 comprises a first ring body 71 and a second ring body 72, the first ring body 71 is fixedly connected to the side surface of the turbine static disc 1 close to the turbine rotary disc 2, and the axis of the first ring body 71 is coincident with the axis of the turbine static disc 1. The side of the first ring body 71 close to the second ring body 72 is fixedly connected with a connecting plate 74, the side of the first ring body 71 far away from the connecting plate 74 is fixedly connected with the second ring body 72, and the axis of the second ring body 72 is superposed with the axis of the first ring body 71. The side surfaces of the first ring body 71 and the second ring body 72, which are close to each other, are provided with a plurality of flow guide ring grooves 73, the axis of each flow guide ring groove 73 is overlapped with the axis of the first ring body 71, and the flow guide ring grooves 73 on the first ring body 71 and the flow guide ring grooves 73 on the second ring body 72 are symmetrically arranged relative to the connecting plate 74.
Referring to fig. 6, a plurality of shunting ring bodies 75 are fixedly connected to the connecting plate 74, the shunting ring bodies 75 correspond to the guide ring grooves 73 one to one, and the end portions of the shunting ring bodies 75 far away from the connecting plate 74 are disposed in the guide ring grooves 73. The side of reposition of redundant personnel annulus 75 near connecting plate 74 sets up vertically, and the side that reposition of redundant personnel annulus 75 kept away from connecting plate 74 is circular-arc, and the interval between the side that reposition of redundant personnel annulus 75 kept away from connecting plate 74 and the inside wall of corresponding water conservancy diversion annular groove 73 is certain. A plurality of arc-shaped grooves 751 are formed in the side face, far away from the connecting plate 74, of the flow dividing ring body 75, the arc-shaped grooves 751 are arranged at intervals, and the Tesla valve channel 4 is formed by combining a plurality of flow guide ring grooves 73.
Referring to fig. 6, a plurality of flow dividing members 8 are fixedly connected to the connecting plate 74, the flow dividing members 8 are disposed at intervals, the flow dividing members 8 are disposed between the first ring body 71 and the second ring body 72, and each flow dividing member 8 includes a first flow dividing plate 81 and a second flow dividing plate 82. The first splitter plate 81 is disposed on the side surface of the second splitter plate 82 close to the sealing ring 5, the end portions of the first splitter plate 81 and the second splitter plate 82 far away from each other are blade-shaped, and the end portion of the first splitter plate 81 close to the second splitter plate 82 is arc-shaped.
Referring to fig. 5 and 6, when the high-temperature fuel gas enters the tesla valve channel 4 from the gas outlet of the tesla valve channel 4, the high-temperature fuel gas is divided by the first flow dividing plate 81, and a part of the high-temperature fuel gas impacts along the arc surface of the first flow dividing plate 81, so as to block the circulation of the high-temperature fuel gas. The high-temperature gas through first splitter plate 81 shunts once more when shunting ring body 75, and shunting ring body 75 is provided with the reposition of redundant personnel efficiency that does benefit to the high-temperature gas that improves, and shunting ring body 75's setting makes the high-temperature gas that gets into water conservancy diversion annular groove 73 hug closely the inside wall flow of water conservancy diversion annular groove 73 to make the gas of reposition of redundant personnel concentrate more when flowing out water conservancy diversion annular groove 73, and then improve the separation effect to mainstream high-temperature gas. The arc-shaped groove 751 deflects the flowing direction of the high-temperature fuel gas entering the diversion ring groove 73, thereby offsetting part of the high-temperature fuel gas and reducing the speed of the diverted fuel gas.
Referring to fig. 5 and 6, when the sealed cold air enters the tesla valve channel 4 through the air inlet of the tesla valve channel 4, the second diversion plate 82 diverts the sealed cold air, and the two sealed cold air correspond to the two high-temperature gas, so as to block the flow of the high-temperature gas. The Tesla valve channel 4 is arranged to be beneficial to blocking high-temperature gas from entering the disc cavity, so that the amount of sealed cold gas can be properly reduced, the reliable sealing effect is guaranteed by the amount of smaller sealed cold gas, and the starting efficiency of the turbine is improved.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: equivalent changes in structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (3)
1. The utility model provides a structure of obturating of gas turbine wheel rim, includes turbine quiet dish (1), turbine carousel (2), turbine quiet dish (1) with be provided with clearance, its characterized in that between turbine carousel (2): a positioning ring (3) is arranged between the turbine static disc (1) and the turbine rotary disc (2), a Tesla valve channel (4) is arranged in the positioning ring (3), an air inlet of the Tesla valve channel (4) is communicated with the inner side wall of the positioning ring (3), and an air outlet of the Tesla valve channel (4) is communicated with the outer side wall of the positioning ring (3);
the positioning ring (3) comprises a first ring body (71) fixedly connected to the turbine static disc (1) and a second ring body (72) arranged on the first ring body (71), a connecting plate (74) is arranged between the first ring body (71) and the second ring body (72), a plurality of flow guide ring grooves (73) are formed in the side faces, close to each other, of the first ring body (71) and the second ring body (72), and the Tesla valve channel (4) is composed of the flow guide ring grooves (73);
a plurality of reposition of redundant personnel ring bodies (75) of fixedly connected with on connecting plate (74), reposition of redundant personnel ring body (75) with water conservancy diversion annular groove (73) one-to-one, reposition of redundant personnel ring body (75) set up in water conservancy diversion annular groove (73), just the surface of reposition of redundant personnel ring body (75) with corresponding interval between the inside wall of water conservancy diversion annular groove (73) is certain, reposition of redundant personnel ring body (75) are close to the spaced apart arc wall (751) that is equipped with on the side of the gas outlet of tesla valve passageway (4).
2. A gas turbine disk rim seal structure according to claim 1, wherein: fixedly connected with reposition of redundant personnel piece (8) on connecting plate (74), reposition of redundant personnel piece (8) including set up in ring body (71) with first reposition of redundant personnel board (81) and second reposition of redundant personnel board (82) between ring body two (72), first reposition of redundant personnel board (81) with the tip that second reposition of redundant personnel board (82) kept away from each other is blade of a knife or a sword form, first reposition of redundant personnel board (81) are kept away from the tip of tesla valve passageway (4) gas outlet is circular-arc.
3. A gas turbine disk rim seal structure according to claim 1, wherein: the turbine static disc (1) and the turbine rotary disc (2) are fixedly connected with sealing rings (5), and the sealing rings (5) are arranged in a staggered mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210521593.0A CN114909188B (en) | 2022-05-13 | 2022-05-13 | Sealing structure for rim of turbine disc of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210521593.0A CN114909188B (en) | 2022-05-13 | 2022-05-13 | Sealing structure for rim of turbine disc of gas turbine |
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| Publication Number | Publication Date |
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| CN114909188A CN114909188A (en) | 2022-08-16 |
| CN114909188B true CN114909188B (en) | 2023-02-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210521593.0A Active CN114909188B (en) | 2022-05-13 | 2022-05-13 | Sealing structure for rim of turbine disc of gas turbine |
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| EP3135869A1 (en) * | 2015-08-25 | 2017-03-01 | Rolls-Royce Deutschland Ltd & Co KG | Sealing element for a turbomachine, corresponding turbomachine and manufacturing process |
| CN213654925U (en) * | 2020-12-03 | 2021-07-09 | 西安交通大学 | End wall slot shaping structure at disc cavity sealing outlet |
| CN113236373A (en) * | 2021-06-07 | 2021-08-10 | 西北工业大学 | Tesla valve-based air film hole channel structure and application thereof to turbine blade leading edge |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080061515A1 (en) * | 2006-09-08 | 2008-03-13 | Eric Durocher | Rim seal for a gas turbine engine |
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| EP3135869A1 (en) * | 2015-08-25 | 2017-03-01 | Rolls-Royce Deutschland Ltd & Co KG | Sealing element for a turbomachine, corresponding turbomachine and manufacturing process |
| CN213654925U (en) * | 2020-12-03 | 2021-07-09 | 西安交通大学 | End wall slot shaping structure at disc cavity sealing outlet |
| CN113236373A (en) * | 2021-06-07 | 2021-08-10 | 西北工业大学 | Tesla valve-based air film hole channel structure and application thereof to turbine blade leading edge |
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