CN114934813A - Partial air inlet axial flow impulse turbine and blade tip clearance loss active control method thereof - Google Patents
Partial air inlet axial flow impulse turbine and blade tip clearance loss active control method thereof Download PDFInfo
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- CN114934813A CN114934813A CN202210461315.0A CN202210461315A CN114934813A CN 114934813 A CN114934813 A CN 114934813A CN 202210461315 A CN202210461315 A CN 202210461315A CN 114934813 A CN114934813 A CN 114934813A
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- 238000000034 method Methods 0.000 title claims description 21
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 84
- 238000007789 sealing Methods 0.000 claims abstract description 30
- 239000007921 spray Substances 0.000 claims abstract description 27
- 238000005553 drilling Methods 0.000 claims abstract description 11
- 238000005507 spraying Methods 0.000 claims abstract description 7
- 239000007788 liquid Substances 0.000 claims description 33
- 244000126211 Hericium coralloides Species 0.000 claims description 10
- 230000006698 induction Effects 0.000 claims description 4
- 230000000717 retained effect Effects 0.000 claims description 2
- 238000006243 chemical reaction Methods 0.000 abstract description 9
- 230000008878 coupling Effects 0.000 abstract description 4
- 238000010168 coupling process Methods 0.000 abstract description 4
- 238000005859 coupling reaction Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 24
- 239000003380 propellant Substances 0.000 description 6
- 238000001816 cooling Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000002195 synergetic effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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Classifications
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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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
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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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
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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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention discloses a single-stage axial flow impulse turbine with partial air inlet, which comprises a hollow casing with a cylindrical structure, wherein the middle part of the casing is coaxially connected with an impeller, the edge of the impeller is provided with a cascade runner to form an impulse cascade, an axial gap is formed between the surface of the impeller and the surface of the casing, the side edge of the impeller and the casing form a blade top gap, the side wall of the impeller, which is right opposite to the casing, is connected with an impeller shroud, the inside of the casing, which is right opposite to the side wall of the impeller, is connected with an inner shroud of the casing, the impeller shroud and the inner shroud of the casing form a labyrinth seal structure, the side wall of the casing, which is right opposite to the side wall of the impeller, is provided with a plurality of casing water spray nozzles, one surface of the casing, which faces towards the impeller, is provided with a drilling spray pipe, and the casing faces to a special-shaped exhaust outlet on the other surface of the impeller; through the coupling control of the grate sealing structure and the water spraying opening of the casing, the loss of the blade top clearance can be reduced to the maximum extent, the effective efficiency of the turbine is improved, and the energy conversion capability of the turbine is enhanced.
Description
Technical Field
The invention belongs to the technical field of gas turbine engines in a thermodynamic system of an underwater vehicle, and particularly relates to a single-stage axial flow impulse turbine with partial air intake, and further relates to an active control method for blade tip clearance loss of the single-stage axial flow impulse turbine with partial air intake.
Background
The thermodynamic underwater vehicle continuously pursues higher speed, range and depth performance since birth. Among these, the thermodynamic system is an important system for providing navigation power, and the merits of the thermodynamic system will directly determine the maneuvering characteristics of the aircraft. Because the working environment of the underwater vehicle is underwater, the volume and the mass of the underwater vehicle are limited for pursuing higher performance, and meanwhile, the underwater vehicle also needs to carry propellant during the sailing process, the improvement of the specific energy and the specific power of a thermodynamic system is particularly important.
The method for improving the specific energy and specific power characteristics of the thermodynamic system mainly comprises two methods, namely improving the energy characteristics of the propellant and improving the heat-power conversion effectiveness of the engine. Since the improvement in propellant performance is often a revolutionary advance, slow and difficult, engineering generally improves powertrain performance from an engine performance standpoint.
The gas turbine engine for underwater vehicles is a single-stage axial-flow impulse turbine with partial intake, which is characterized by small volume and short blades. In order to increase the mass of propellant required per unit of useful power delivered by the power plant per unit of time, i.e. to increase the specific consumption of propellant by the power plant, in view of the efficiency of the conversion of the engine thermal power into useful power, it is necessary to reduce the losses during the operation of the turbine. The flow loss generated by the partial inlet axial flow turbine during operation mainly comprises nozzle loss, bucket loss, partial inlet loss, blade tip clearance loss and the like. In the gas turbine engine for an underwater vehicle, tip clearance loss is more serious because the aspect ratio of the blade is small. Reducing tip clearance losses facilitates increasing turbine efficiency to increase power system performance.
At present, the technology for reducing the turbine blade top clearance loss is provided with blade top gas jet and blade top sealing structure means, and the application scenes of the technology are full-cycle air inlet axial flow turbines and radial flow turbines with larger scale. Because the working environment of the underwater vehicle is underwater, the underwater vehicle has limited propellant carrying capacity, and cannot perform gas jet by using air in the atmosphere like an aviation turbine. In addition, because the size of part of the air inlet axial flow turbine is small, the blade top sealing structure of the large-size turbine and the complicated jet flow channel in the blade cannot be used. Therefore, none of the prior art is able to control for loss of gas turbine tip clearance for underwater vehicles.
Disclosure of Invention
The invention aims to provide a single-stage axial flow impulse turbine with partial air inlet, and solves the problem of low energy conversion efficiency of the partial air inlet axial flow turbine due to large blade tip clearance loss.
It is another object of the present invention to provide a method of active tip clearance loss control for a single stage axial flow impulse turbine with partial induction.
The invention adopts the technical scheme that the single-stage axial flow impulse turbine with partial air inlet comprises a hollow casing with a cylindrical structure, wherein the middle part of the casing is coaxially connected with an impeller, the edge of the impeller is provided with a cascade runner to form an impulse type cascade, an axial gap is formed between the surface of the impeller and the surface of the casing, a blade top gap is formed between the side edge of the impeller and the side wall of the casing, the side wall of the impeller, which is right opposite to the casing, is connected with an impeller shroud, the inner shroud of the casing, which is right opposite to the side wall of the impeller, is connected with the inner shroud of the casing, the impeller shroud and the inner shroud of the casing form a labyrinth seal structure, the side wall of the casing, which is right opposite to the side wall of the impeller, is provided with a plurality of casing water spray ports, one surface of the casing, which faces towards the impeller, is provided with a drilling spray pipe, and the casing faces to the other surface of the impeller and faces towards a special-shaped exhaust outlet.
The invention is also characterized in that:
the impeller shroud and the inner shroud of the casing are formed by grid teeth, and the grid teeth of the impeller shroud and the grid teeth of the inner shroud of the casing are distributed in a staggered mode to form a labyrinth grid tooth sealing structure.
The main projection shape of the comb tooth is isosceles trapezoid.
The number of the casing water spray nozzles is four, and the distance between every two adjacent casing water spray nozzles is 90 degrees.
According to the other technical scheme adopted by the invention, the active control method for the blade top clearance loss of the single-stage axial flow impulse turbine with partial air inlet is characterized in that liquid water sprayed out from a water spraying port of a casing is retained in a labyrinth seal structure to form a liquid seal film by adjusting parameters of a labyrinth seal structure formed by an impeller shroud and a shroud in the casing and parameters of a water spraying port of the casing.
The parameters of the comb tooth sealing structure comprise the number of comb teeth of the impeller shroud and the shroud in the casing, the height of the comb teeth, the distance between the comb teeth, the width of the tooth top and the included angle of the tooth top.
The parameters of the water jet of the casing comprise the shape of the water jet, the position of the water jet, the distance between the water jets and the flow rate of the water jet.
The invention has the beneficial effects that:
according to the single-stage axial flow impulse turbine with partial air intake, the comb tooth sealing structure and the casing water jet are matched for use and can be mutually coupled, and the liquid seal phenomenon formed after the combination of the comb tooth groove and liquid water can reduce the blade top gap loss to the maximum extent and improve the energy conversion capability of the turbine; different from a blade top jet control method, the control mode of a casing water jet can meet the requirements of the working environment of an underwater vehicle, and liquid water in the environment is fully utilized; the loss of the gas turbine for the underwater vehicle is dynamically controlled, the gas turbine can be controlled in the design working condition and non-design working condition operation process of the turbine at the same time, and the problem that the energy conversion efficiency is low due to the fact that the blade top clearance loss of part of the air inlet axial flow turbine is large is solved.
Drawings
FIG. 1 is a schematic view of a single stage axial flow impulse turbine with partial induction according to the present invention;
FIG. 2 is a cross-sectional view of a single stage axial flow impulse turbine with partial induction of the present invention;
FIG. 3 is a structural schematic view of a labyrinth seal structure according to the present invention;
FIG. 4 is a schematic view of the position of the water jet of the casing of the present invention.
In the figure, 1, an impeller, 2, a casing, 3, a drilling nozzle, 4, a special-shaped exhaust outlet, 5, an impeller shroud, 6, a casing inner shroud, 7, a casing water jet, 8, an axial gap, 9, a blade grid flow passage, 10, a grid tooth sealing structure, 11, a first casing water jet, 12, a second casing water jet, 13, a third casing water jet, 14 and a fourth casing water jet.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention relates to a single-stage axial flow impulse turbine with partial air intake, namely a gas turbine for a controlled underwater vehicle, which comprises a hollow cylindrical structure casing 2 as shown in figures 1 and 2, wherein the middle part of the casing 2 is coaxially connected with an impeller 1, a gap between the two forms a turbine through-flow area, a cascade runner 9 is arranged at the edge of the impeller 1 to form an impulse cascade, specifically, a certain number of working blades which are arranged on a wheel disc, have the same shape and are arranged according to a certain pitch, the size parameters of the blades, the line type of the blades, the installation angle, the pitch and the like are determined according to the design parameters of the turbine, an axial gap 8 is formed between the surface of the impeller 1 and the surface of the casing 2, the side edge of the impeller 1 and the casing 2 form a blade top gap, the position of the side wall of the impeller 1, which is opposite to the casing 2, is connected with an impeller shroud 5 (in the blade top gap), the side wall of the casing 2, which is opposite to the side wall of the impeller 1, is connected with a casing inner shroud 6 (in the blade top gap), the impeller shroud 5 and the casing inner shroud 6 form a comb tooth sealing structure 10, the side wall of the casing 2 opposite to the side wall of the impeller 1 is provided with a plurality of casing water spray nozzles 7, one surface of the casing 2 facing the impeller 1 is provided with a drilling spray pipe 3, and the other surface of the casing 2 facing the impeller 1 is provided with a special-shaped exhaust outlet 4.
In the invention, the labyrinth seal structure 10 can be tightly combined with liquid water sprayed from the casing water spray opening 7, which is particularly characterized in that the liquid water sprayed from the casing water spray opening 7 is accumulated in a labyrinth groove to carry out liquid seal on blade top gaps, so that the blade top gap size is further reduced, and the blade top gap loss is greatly reduced. Compared with the blade top clearance loss control mode of the traditional aviation turbine, the blade top clearance loss control method can fully utilize the characteristic that the liquid water density is higher than that of gas, so that the two control modes do not have common superposition on the reduction of the blade top clearance loss, but have a positive synergistic effect of mutual coupling. Meanwhile, the sprayed liquid water also has a certain cooling effect, so that the expansion of the impeller 1 and the grate sealing structure 10 can be reduced, and the collision condition of the rotating part and the casing 2 is prevented.
The impeller shroud band 5 and the casing inner shroud band 6 are both formed by grid teeth, the main projection shape of the grid teeth is isosceles trapezoid, the grid teeth of the impeller shroud band 5 and the casing inner shroud band 6 are distributed in a staggered mode to form a labyrinth-shaped grid tooth sealing structure 10, the labyrinth-shaped grid tooth sealing structure 10 can be tightly combined with liquid water sprayed from the casing water spraying port 7, and the liquid water sprayed from the casing water spraying port 7 can be accumulated in a grid tooth groove to perform liquid sealing on blade top gaps, so that the blade top gap size is further reduced, and the blade top gap loss is greatly reduced. Compared with the blade top clearance loss control mode of the traditional aviation turbine, the blade top clearance loss control method can fully utilize the characteristic that the liquid water density is higher than that of gas, so that the two control modes do not have common superposition on the reduction of the blade top clearance loss, but have a positive synergistic effect of mutual coupling. Meanwhile, the sprayed liquid water also has a certain cooling effect, so that the expansion of the impeller 1 and the labyrinth seal structure 10 can be reduced, and the collision condition of the rotating part and the casing 2 is prevented.
The single-stage axial-flow impulse turbine of partial inlet air of the invention is a gas turbine for controlled underwater vehicles, and because of the characteristic of partial inlet air, not all the blades have air flowing through so that they operate simultaneously. The arc section directly opposite to the drilling nozzle 3 is continuously provided with airflow passing through the working blade in the working process, so the arc section is called an air inlet working section, and the arc section which is not covered by the drilling nozzle is called a non-air inlet working section. The losses controlled by the present invention occur mainly in the intake working section.
The casing water spray ports 7 are through holes penetrating through the inner surface and the outer surface of the casing 2, the number of the four casing water spray ports 7 is four, the distance between every two adjacent casing water spray ports 7 is 90 degrees, one of the water spray ports is arranged in the middle of the casing corresponding to the air inlet working section, and the rest water spray ports are located in the non-air inlet working section.
As shown in figure 2, in the air inlet working section, the drilling nozzle 3 arranged at the upstream of the impeller 1 is a convergent-divergent nozzle, after high-temperature and high-pressure gas in the combustion chamber passes through the drilling nozzle 3, the available enthalpy drop of the gas is converted into kinetic energy, after the gas at the outlet of the drilling nozzle 3 is accelerated, the absolute speed of the gas exceeds the sonic speed, as shown in figure 3, then the gas flows into a cascade channel 9 through an axial gap 8 between the drilling nozzle 3 and the impeller 1, and as part of the air inlet axial flow turbine uses an impulse type cascade, after the gas passes through the cascade channel 9, the impeller 1 rotates only under the impulse action of the gas flow, and the kinetic energy of the gas is converted into mechanical work. Since the flow area directly communicating with the axial gap 8 includes the tip gap formed between the impeller 1 and the side wall of the casing 2 in addition to the cascade channel 9, and there is a pressure difference between upstream and downstream of the tip gap during operation of the turbine, the supersonic combustion gas does not completely pass through the cascade channel 9, and a small amount of gas leaks from the tip gap to the back cavity, which is a cause of tip gap loss.
In order to reduce the blade tip clearance loss of the partial air inlet axial flow turbine, the invention provides a blade tip clearance loss active control method of a partial air inlet single-stage axial flow impulse turbine, a controllable grate tooth sealing structure 10 arranged at the top of an impeller 1, and a casing water jet 7 arranged on a casing 2 and penetrating through the inner surface and the outer surface.
Based on the above, the invention provides an active control method for blade tip clearance loss of a partially-air-intake single-stage axial flow impulse turbine, which is characterized in that parameters of a labyrinth seal structure 10 formed by an impeller shroud 5 and a casing inner shroud 6 and parameters of a casing water spray opening 7 are adjusted, so that liquid water sprayed from the casing water spray opening 7 stays in the labyrinth seal structure 10 to form a liquid sealing film.
The parameters of the labyrinth seal structure 10 and the parameters of the casing water spray nozzle 7 are shown in fig. 3, the chord length of the blade is 10a, the number of the labyrinth of the impeller shroud 5 is 3, the height of the labyrinth is 9/4a, the distance between the teeth is 8/5a, the tooth top width is 1/2a, and the tooth top included angle is 30 degrees. The impeller shroud 5 is arranged at a specific position higher than the blade top 6/5a, and the central axis of the first tooth is away from the plane 9/4a where the inlet of the cascade flow passage 9 is located. The number of the grid teeth of the inner shroud ring 6 of the casing is 2, the height of the grid teeth is 9/4a, the distance between the grid teeth is 8/5a, the width of the tooth top is 1/2a, and the tooth top included angle is 30 degrees. The specific position where the inner shroud 6 of the casing is disposed is on the inner surface of the casing. Specific controllable contents of the blade tip sealing structure 6 include: the number of the comb teeth, the height of the comb teeth, the distance between the comb teeth, the width of the tooth top and the included angle of the tooth top.
The parameters of the grate sealing structure 10 comprise the number of grates of the impeller shroud 5 and the shroud 6 in the casing, the height of the grates, the distance between the grates, the width of the tooth tops and the included angle of the tooth tops.
The parameters of the casing water jet 7 include the shape of the water jet, the position of the water jet, the distance between the water jets and the flow rate of the water jet.
When the turbine works, although the total differential pressure at two sides of the grate sealing structure 10 corresponding to the air inlet working section is not changed, the differential pressure between the grooves of the adjacent grates is reduced due to the division of the grates. Meanwhile, the gap can be kept as small as possible, because the section of the comb tooth is trapezoidal, the tooth top is thin, and even if the impeller shroud band 5 and the inner shroud band 6 of the casing collide with each other due to thermal expansion, no serious result can be caused. Thus, the pressure difference is reduced, and the air leakage area is reduced, so that the air leakage is effectively reduced, and the blade tip clearance loss is reduced. In addition, the labyrinth seal structure 10 can eliminate the mixing loss of leakage flow and main flow caused by the pressure difference between the suction surface and the pressure surface of the front and rear cascade flow passages.
When the turbine works, the water jet 11 of the first casing of the air inlet working section can directly reduce the size of the blade top clearance, and the loss of the blade top clearance of the air inlet working section is reduced. Liquid water sprayed from the second casing water spray port 12, the third casing water spray port 13 and the fourth casing water spray port 14 of the non-air-intake working section stays in the labyrinth seal structure 10 and flows to the air-intake working section along with the rotation of the impeller 1, so that the blade tip clearance loss of the air-intake working section is reduced. The arrangement position of the water spray nozzles in the non-air-intake working section is more critical, the liquid water enters the turbine too early to block the rotation of the impeller 1, and enters the turbine too late to miss the air-intake working section to control the loss of the blade top gap.
In addition, when the turbine works, the water pump can be driven by the turbine to introduce liquid water in the working environment of the underwater vehicle into the vehicle, and the liquid water is supplied to the water inlet on the outer surface of the casing of the turbine through a pipeline, so that the characteristic that a large amount of liquid water exists in the working environment of the underwater vehicle is fully utilized. Meanwhile, the material sprayed out of the water spray opening is liquid water, the mass flow of the liquid water can be actively adjusted according to the blade top state of the impeller, and the gap loss of the blade top of the turbine under the design working condition and the non-design working condition is controlled.
The important characteristic of the invention is that the sealing and cooling function of liquid water in underwater working environment can be fully utilized, and the comb tooth sealing structure 10 combined with the casing water jet 7 can form a liquid sealing film at the blade top gap. The active control effect on the blade top clearance loss is better than that of a common labyrinth seal structure of the aircraft turbine, so that the blade top clearance loss of the turbine for the underwater vehicle can be further reduced. The advantage is that the liquid sealing film is formed by the synergistic effect of the two structures, so that on one hand, the sealing effect is far greater than that of the single-use labyrinth sealing structure 10; on the other hand, the liquid sealing film plays a role in cooling, expansion of the impeller 1 and the labyrinth sealing structure 10 is reduced, and collision between the rotating component and the casing 2 is prevented.
Through the mode, the part of the air inlet single-stage axial flow impulse turbine, the comb tooth sealing structure and the casing water spray nozzle are matched for use and can be mutually coupled, and the liquid seal phenomenon formed after the combination of the comb tooth groove and liquid water can reduce the blade top gap loss to the maximum extent and improve the energy conversion capability of the turbine; different from a blade top jet control method, the control mode of a casing water jet can meet the requirements of the working environment of an underwater vehicle, and liquid water in the environment is fully utilized; the loss of the gas turbine for the underwater vehicle is dynamically controlled, the gas turbine can be controlled in the design working condition and non-design working condition operation processes of the turbine at the same time, and the problem of low energy conversion efficiency caused by large loss of blade top gaps of part of air inlet axial flow turbines is solved; the active control method for the blade top clearance loss of the single-stage axial flow impulse turbine with partial air intake can control the blade top clearance loss of the gas turbine for the underwater vehicle in various modes. Through the coupling control of the grate sealing structure and the water spraying opening of the casing, the loss of the blade top clearance can be reduced to the maximum extent, the effective efficiency of the turbine is improved, and the energy conversion capability of the turbine is enhanced.
Claims (7)
1. The single-stage axial flow impulse turbine with partial air inlet is characterized by comprising a hollow casing (2) with a cylindrical structure, wherein the middle part of the casing (2) is coaxially connected with an impeller (1), the edge of the impeller (1) is provided with a cascade runner (9) to form an impulse cascade, an axial gap (8) is formed between the surface of the impeller (1) and the surface of the casing (2), a blade tip gap is formed between the side edge of the impeller (1) and the side wall of the casing (2), the side wall of the impeller (1) right opposite to the casing (2) is connected with an impeller shroud (5), the side wall of the casing (2) right opposite to the impeller (1) is connected with a casing inner shroud (6), the impeller shroud (5) and the casing inner shroud (6) form a comb tooth sealing structure (10), and a plurality of casing water spraying ports (7) are formed on the side wall of the casing (2) right opposite to the side wall of the impeller (1), a drilling spray pipe (3) is arranged on one surface of the casing (2) facing the impeller (1), and a special-shaped exhaust outlet (4) is arranged on the other surface of the casing (2) facing the impeller (1).
2. The single-stage axial-flow impulse turbine of claim 1, characterized in that the impeller shroud (5) and the casing inner shroud (6) are formed by grid teeth, and the grid teeth of the impeller shroud (5) and the casing inner shroud (6) are distributed in a staggered manner to form a labyrinth-shaped grid tooth sealing structure (10).
3. The single stage axial flow impulse turbine of claim 2, wherein said main projection of said labyrinth is in the shape of an isosceles trapezoid.
4. The partially-aspirated single-stage axial-flow impulse turbine of claim 1, characterized in that the casing water jets (7) are four, and two adjacent casing water jets (7) are 90 ° apart.
5. The active control method for the tip clearance loss of the partially-charged single-stage axial flow impulse turbine is characterized in that parameters of a labyrinth seal structure (10) formed by an impeller shroud (5) and a casing inner shroud (6) and parameters of a casing water spray opening (7) are adjusted, so that liquid water sprayed from the water spray opening of the casing (2) is retained in the labyrinth seal structure (10) to form a liquid sealing film.
6. The active control method for the tip clearance loss of the partially-charged single-stage axial-flow impulse turbine according to claim 5, characterized in that the parameters of the labyrinth seal structure (10) comprise the number of labyrinth teeth, the height of the labyrinth teeth, the distance between the teeth, the width of the tooth top and the included angle of the tooth top of the shroud (5) and the shroud (6) in the casing.
7. The method of active tip clearance loss control for a single stage axial flow impulse turbine with partial induction as set forth in claim 5, characterized in that the casing water jet (7) parameters include water jet shape, water jet position, inter-water jet distance, and water jet flow.
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| CN202210461315.0A CN114934813B (en) | 2022-04-28 | 2022-04-28 | Partial inlet axial flow impulse turbine and active control method for clearance loss of blade tip of partial inlet axial flow impulse turbine |
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| CN202210461315.0A CN114934813B (en) | 2022-04-28 | 2022-04-28 | Partial inlet axial flow impulse turbine and active control method for clearance loss of blade tip of partial inlet axial flow impulse turbine |
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| CN114934813B (en) | 2023-12-01 |
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