CN114934813B - Partial inlet axial flow impulse turbine and active control method for clearance loss of blade tip of partial inlet axial flow impulse turbine - Google Patents
Partial inlet axial flow impulse turbine and active control method for clearance loss of blade tip of partial inlet axial flow impulse turbine Download PDFInfo
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- CN114934813B CN114934813B CN202210461315.0A CN202210461315A CN114934813B CN 114934813 B CN114934813 B CN 114934813B CN 202210461315 A CN202210461315 A CN 202210461315A CN 114934813 B CN114934813 B CN 114934813B
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- 238000000034 method Methods 0.000 title claims description 15
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 81
- 238000007789 sealing Methods 0.000 claims abstract description 37
- 244000126211 Hericium coralloides Species 0.000 claims abstract description 28
- 239000007921 spray Substances 0.000 claims abstract description 15
- 238000005553 drilling Methods 0.000 claims abstract description 10
- 239000007788 liquid Substances 0.000 claims description 31
- 238000005507 spraying Methods 0.000 claims description 8
- 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
- 239000003380 propellant Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000001816 cooling Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000002195 synergetic effect Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 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
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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 intake, which comprises a hollow and cylindrical casing, wherein the middle part of the casing is coaxially connected with an impeller, a blade grid runner is formed at the edge of the impeller to form impulse blade grids, 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 casing, the side wall of the impeller is opposite to the casing and is connected with an impeller shroud, the side wall of the casing is opposite to the impeller and is connected with an inner shroud of the casing, the impeller shroud and the inner shroud of the casing form a grate seal structure, a plurality of casing water spray openings are formed on the side wall of the casing opposite to the impeller, a drilling spray pipe is formed on one surface of the casing facing the impeller, and a special-shaped exhaust outlet is formed on the casing facing the other surface of the impeller; through the coupling control of the comb tooth sealing structure and the casing water jet, the clearance loss of the blade top can be reduced to the greatest 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 thermodynamic systems of underwater vehicles, and particularly relates to a single-stage axial flow impulse turbine with partial air intake, and also relates to an active control method for blade tip clearance loss of the single-stage axial flow impulse turbine with partial air intake.
Background
Thermodynamic underwater vehicles have been pursuing higher speed, range and depth performance since birth. Among them, the thermal power system is an important system for providing navigation power for the thermal power system, and the advantages and disadvantages of the power system directly determine the maneuvering performance of the aircraft. Because the working environment of an underwater vehicle is underwater, the volume and the mass of the underwater vehicle are limited in order to pursue higher performance, and meanwhile, the underwater vehicle also needs to carry a propellant during the course of navigation, so that the improvement of specific energy and specific power of a thermodynamic system is particularly important.
There are two main methods for improving the specific energy and specific power characteristics of the thermodynamic system, the first is to improve the energy characteristics of the propellant, and the second is to improve the heat-power conversion effectiveness of the engine. Since the improvement in propellant performance is often a revolutionary advance, it is relatively slow and difficult, and 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 has the characteristics of small volume and short blades. In order to increase the mass of the propellant required by the power plant to deliver a unit of useful power per unit of time, i.e. increase the unit consumption rate of the propellant of the power plant, from the point of view of the efficiency of the thermal power conversion of the engine, it is necessary to reduce the losses during operation of the turbine. The flow losses that occur during operation of a partial intake axial flow turbine mainly include nozzle losses, bucket losses, partial intake losses, tip clearance losses, and the like. In gas turbine engines for underwater vehicles, tip clearance losses are more severe due to the smaller aspect ratio of the blades. Reducing tip clearance losses facilitates improving turbine efficiency to improve power system performance.
Currently, there are technologies that have emerged to reduce turbine tip clearance losses, including tip gas jet and tip seal structural approaches, and these technologies have application scenarios in larger scale full-cycle inlet axial and radial turbines. Because the working environment of the underwater vehicle is underwater, the underwater vehicle is limited in carrying propellant, and the air jet cannot be performed by using the air in the atmosphere like an aviation turbine. In addition, due to the small dimensions of some air-intake axial flow turbines, the tip seal structures and the complex fluidic flow passages inside the blades of large-scale turbines are not available. Thus, none of the prior art is able to control the gas turbine tip clearance losses for underwater vehicles.
Disclosure of Invention
The invention aims to provide a single-stage axial flow impulse turbine with partial air intake, which solves the problem of low energy conversion efficiency of the partial air intake axial flow turbine due to larger blade tip clearance loss.
It is another object of the present invention to provide a method of actively controlling tip clearance losses in a single stage axial flow impulse turbine with partial inlet air.
The invention adopts the technical scheme that the single-stage axial flow impulse turbine with partial air inlet comprises a hollow and cylindrical casing, wherein the middle part of the casing is coaxially connected with an impeller, a blade grid runner is formed at the edge of the impeller to form impulse blade grids, 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 is connected with an impeller shroud directly opposite to the casing, the inside of the casing is connected with an inner shroud of the casing directly opposite to the impeller, the impeller shroud and the inner shroud of the casing form a comb tooth sealing structure, the side wall of the casing is provided with a plurality of casing water nozzles directly opposite to the side wall of the impeller, one surface of the casing facing the impeller is provided with a drilling spray pipe, and the other surface of the casing facing the impeller is provided with a special-shaped exhaust outlet.
The invention is also characterized in that:
the impeller shroud and the inner shroud of the casing are both composed of comb teeth, and the comb teeth of the impeller shroud and the comb teeth of the inner shroud of the casing are distributed in a staggered manner to form a labyrinth-shaped comb tooth sealing structure.
The main projection shape of the comb teeth is isosceles trapezoid.
Four casing water jets are arranged, and two adjacent casing water jets are 90 degrees apart.
According to the other technical scheme, the active control method for the blade tip clearance loss of the single-stage axial flow impulse turbine with partial air intake is characterized in that through adjusting the parameters of the comb tooth sealing structure formed by the impeller shroud and the inner shroud of the casing and the parameters of the water jet of the casing, liquid water sprayed out of the water jet of the casing resides in the comb tooth sealing structure to form a liquid sealing film.
The parameters of the sealing structure of the comb teeth comprise the number of comb teeth, the height of the comb teeth, the distance between tooth teeth, the width of tooth tops and the included angle between tooth tops of the impeller shroud and the inner shroud of the case.
The cartridge receiver water jet parameters include the water jet shape, water jet position, inter-water jet distance, and water jet flow.
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 water jet of the casing are matched and used to be coupled with each other, so that the liquid sealing phenomenon formed by combining the comb tooth groove with liquid water can reduce the clearance loss of the blade top to the greatest extent, and the energy conversion capability of the turbine is improved; different from a blade top air injection control method, the control mode of the water jet of the case can meet the working environment requirement of the underwater vehicle, and liquid water in the environment is fully utilized; the dynamic control of the loss of the gas turbine for the underwater vehicle can control the gas turbine in the running process of the turbine design working condition and the non-design working condition, and the problem that the energy conversion efficiency is low due to the fact that the clearance loss of the blade tip of a part of air inlet axial flow turbine is large is solved.
Drawings
FIG. 1 is a schematic illustration of a single stage axial flow impulse turbine of the present invention with partial inlet air;
FIG. 2 is a cross-sectional view of a single stage axial flow impulse turbine of the present invention with partial inlet air;
FIG. 3 is a schematic view of the structure of the sealing structure of the comb teeth in the invention;
FIG. 4 is a schematic illustration of the location of a receiver spout in accordance with the present invention.
In the drawings, an impeller 1, a casing 2, a drilling jet pipe 3, a special-shaped exhaust outlet 4, an impeller shroud 5, a casing inner shroud 6, a casing water jet 7, an axial gap 8, a blade grid runner 9, a grate seal structure 10, a first casing water jet 11, a second casing water jet 12, a third casing water jet 13, and a fourth casing water jet 14.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention relates to a single-stage axial flow impulse turbine with partial air intake, namely a gas turbine for an underwater vehicle which is controlled, as shown in figures 1 and 2, and the gas turbine comprises a hollow and cylindrical casing 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 blade grid runner 9 is formed at the edge of the impeller 1 to form impulse blade grids, a certain number of working blades which are arranged on a wheel disc and have the same shape and are arranged according to a certain pitch are particularly arranged, dimensional parameters such as blade size, blade linearity, mounting angle and pitch are determined according to turbine design parameters, 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 side wall of the impeller 1 is connected with an impeller shroud 5 (in the blade top gap), the side wall of the casing 2 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 grate sealing structure 10, the side wall of the casing 2 is provided with a plurality of casing water spraying openings 7, the side wall of the casing 2 is provided with a special-shaped nozzle 4 facing the impeller 1 and the other surface of the impeller 2 is provided with a special-shaped outlet 4 facing the impeller 3.
According to the invention, the comb tooth sealing structure 10 can be tightly combined with liquid water sprayed by the casing water spraying port 7, and the liquid water sprayed by the casing water spraying port 7 is accumulated in the comb tooth groove to seal the blade tip gap, so that the blade tip gap size is further reduced, and the blade tip gap loss is greatly reduced. Compared with the traditional control mode of the clearance loss of the blade tip of the aviation turbine, the invention can fully utilize the characteristic that the density of liquid water is higher than that of gas, so that the two control modes are not common superposition but positive synergistic effect of mutual coupling on the reduction of the clearance loss of the blade tip. Meanwhile, the sprayed liquid water also has a certain cooling effect, so that the expansion of the impeller 1 and the comb tooth sealing structure 10 can be reduced, and the collision condition of the rotating part and the casing 2 can be prevented.
The impeller shroud 5 and the casing inner shroud 6 are formed by the comb teeth, the main projection shape of the comb teeth is isosceles trapezoid, the comb teeth of the impeller shroud 5 and the casing inner shroud 6 are distributed in a staggered mode, a labyrinth-shaped comb tooth sealing structure 10 is formed, the labyrinth-shaped comb tooth sealing structure 10 can be tightly combined with liquid water sprayed out of the casing water spraying port 7, liquid water sprayed out of the casing water spraying port 7 is particularly accumulated in a comb tooth groove, and liquid sealing is carried out on a blade top gap, so that the size of the blade top gap is further reduced, and the loss of the blade top gap is greatly reduced. Compared with the traditional control mode of the clearance loss of the blade tip of the aviation turbine, the invention can fully utilize the characteristic that the density of liquid water is higher than that of gas, so that the two control modes are not common superposition but positive synergistic effect of mutual coupling on the reduction of the clearance loss of the blade tip. Meanwhile, the sprayed liquid water also has a certain cooling effect, so that the expansion of the impeller 1 and the comb tooth sealing structure 10 can be reduced, and the collision condition of the rotating part and the casing 2 can be prevented.
In the gas turbine for the controlled underwater vehicle, which is a single-stage axial flow impulse turbine with partial air intake, not all the working blades have air flowing through to make them work simultaneously because of the characteristic of partial air intake. The arc segment facing the drilling nozzle 3 is called the air inlet working segment, and the arc segment not covered by the drilling nozzle is called the non-air inlet working segment, because the air flow continuously passes through the working blades during the working process. The loss controlled by the invention mainly occurs in the air 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, four adjacent casing water spray ports 7 are 90 degrees apart, one water spray port is arranged at the middle position of the casing corresponding to the air inlet working section, and the other water spray ports are positioned at the non-air inlet working section.
In the intake working section, as shown in fig. 2, the drilling nozzle 3 arranged upstream of the impeller 1 is a convergent-divergent nozzle, after the high-temperature 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, the absolute velocity of the gas at the outlet of the drilling nozzle 3 exceeds the sonic velocity after acceleration, as shown in fig. 3, then the gas flows into the cascade flow channel 9 through the axial gap 8 between the drilling nozzle 3 and the impeller 1, and as part of the intake axial flow turbine uses impulse type cascades, the impeller 1 rotates only under the impulse action of the gas flow after the gas passes through the cascade flow channel 9, and the kinetic energy of the gas is converted into mechanical work. Since the through-flow region in direct communication with the axial gap 8 includes, in addition to the cascade flow channel 9, a tip clearance formed between the impeller 1 and the side wall of the casing 2, and a pressure difference exists upstream and downstream of the tip clearance during operation of the turbine, the supersonic gas does not pass entirely through the cascade flow channel 9, and a small amount of gas leaks from the tip clearance to the rear cavity, which is a cause of tip clearance loss.
In order to reduce the clearance loss of the top of the blade of the partial air inlet axial flow turbine, the invention provides an active control method for the clearance loss of the top of the blade of the partial air inlet single-stage axial flow impulse turbine, a controllable comb tooth sealing structure 10 arranged at the top of an impeller 1, and a casing water spray opening 7 arranged at 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 the clearance loss of the blade tip of a single-stage axial flow impulse turbine with partial air intake, and the parameters of a comb seal structure 10 and the parameters of a casing water jet 7 formed by an impeller shroud 5 and a casing inner shroud 6 are adjusted, so that liquid water sprayed out of the casing water jet 7 resides in the comb seal structure 10 to form a liquid seal film.
The parameters of the comb tooth sealing structure 10 and the parameters of the water jet 7 of the casing are shown in figure 3, the chord length of the blade is 10a, the number of comb teeth of the impeller shroud 5 is 3, the height of the comb teeth is 9/4a, the distance between tooth teeth is 8/5a, the width of the tooth top is 1/2a, and the included angle between tooth tops is 30 degrees. The impeller shroud 5 is arranged at a specific position higher than the blade tip 6/5a, and the central axis of the first tooth is located at a distance of 9/4a from the plane in which the inlet of the cascade flow passage 9 is located. The number of the comb teeth of the inner shroud 6 of the case is 2, the height of the comb teeth is 9/4a, the distance between the tooth teeth is 8/5a, the width of the tooth top is 1/2a, and the included angle between the tooth tops is 30 degrees. The specific location of the arrangement of the casing inner shroud 6 is on the casing inner surface. Specific controllable contents of the tip seal 6 include: the number of the comb teeth, the height of the comb teeth, the distance between the teeth, the width of the top of the teeth and the included angle of the tooth tops.
The parameters of the comb tooth sealing structure 10 comprise the number of comb teeth, the height of the comb teeth, the distance between tooth teeth, the width of tooth tops and the included angle between tooth tops of the impeller shroud 5 and the inner shroud 6 of the casing.
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, the total pressure difference at two sides of the comb tooth sealing structure 10 corresponding to the air inlet working section is not changed, but the pressure difference between adjacent comb tooth grooves is reduced due to the division of the comb teeth. At the same time, the clearance can be kept as small as possible, because the cross section of the comb teeth is trapezoidal, the tooth tops are thinner, and even if the impeller shroud 5 and the inner shroud 6 of the casing are in collision due to the heating expansion, serious consequences can not be caused. Therefore, the pressure difference is reduced, and the air leakage area is reduced, so that the air leakage is effectively reduced, and the loss of the clearance at the top of the blade is reduced. In addition, the labyrinth seal structure 10 can eliminate the mixing loss of the leakage flow and the main flow caused by the pressure difference between the suction surface and the pressure surface of the front blade grid runner and the rear blade grid runner.
When the turbine works, the first casing water jet 11 of the air inlet working section can directly reduce the size of the blade tip clearance, and the blade tip clearance loss of the air inlet working section is reduced. Liquid water sprayed out of 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 inlet working section can reside in the comb tooth sealing structure 10 and flow to the air inlet working section along with rotation of the impeller 1, so that the blade tip clearance loss of the air inlet working section is reduced. The water jet layout position in the non-air-intake working section is more critical, and liquid water enters the turbine too early to prevent the rotation of the impeller 1, and enters the turbine too late to miss the air-intake working section and cannot control the blade tip clearance loss.
In addition, the turbine can drive the water pump to introduce liquid water in the working environment of the underwater vehicle into the vehicle during working, and the liquid water is supplied to the water inlet on the outer surface of the turbine casing through the 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 water jet spouts out the material and is liquid water, and the mass flow can be actively regulated according to the blade tip state of the impeller, and meanwhile, the clearance loss of the blade tip of the turbine under the design working condition and the non-design working condition is controlled.
The invention has the important characteristic that the sealing and cooling effects of liquid water in the underwater working environment can be fully utilized, and the comb tooth sealing structure 10 combined with the casing water spraying port 7 can form a liquid sealing film at the blade top gap. The active control effect on the clearance loss of the blade tip is superior to that of a comb tooth sealing structure commonly used in an aero turbine, so that the clearance loss of the blade tip of the turbine for an 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 comb tooth sealing structure 10; on the other hand, the liquid sealing film plays a role in reducing the temperature, reduces the expansion of the impeller 1 and the comb tooth sealing structure 10, and prevents the collision condition of the rotating part and the casing 2.
Through the mode, the single-stage axial flow impulse turbine with partial air intake can be mutually coupled through the cooperation of the grate sealing structure and the casing water jet, and the liquid sealing phenomenon formed after the grate groove and the liquid water are combined can reduce the clearance loss of the top of the blade to the greatest extent, so that the energy conversion capability of the turbine is improved; different from a blade top air injection control method, the control mode of the water jet of the case can meet the working environment requirement of the underwater vehicle, and liquid water in the environment is fully utilized; the loss of the gas turbine for the underwater vehicle is dynamically controlled, and the gas turbine can be controlled in the running process of the turbine design working condition and the non-design working condition at the same time, so that the problem of low energy conversion efficiency caused by the large blade tip clearance loss of a part of the air inlet axial flow turbine is solved; the active control method for the tip clearance loss of the single-stage axial flow impulse turbine with partial air intake can control the tip clearance loss of the gas turbine for the underwater vehicle in various modes. Through the coupling control of the comb tooth sealing structure and the casing water jet, the clearance loss of the blade top can be reduced to the greatest extent, the effective efficiency of the turbine is improved, and the energy conversion capability of the turbine is enhanced.
Claims (2)
1. The single-stage axial flow impulse turbine with partial air intake is characterized by comprising a hollow and cylindrical casing (2), wherein the middle part of the casing (2) is coaxially connected with an impeller (1), a blade grid runner (9) is formed at the edge of the impeller (1) to form impulse blade grids, an axial gap (8) is formed between the surface of the impeller (1) and the surface of the casing (2), a blade top 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) is connected with an impeller shroud (5) opposite to the casing (2), the side wall of the casing (2) is connected with a casing inner shroud (6) opposite to the impeller (1), the impeller shroud (5) and the casing inner shroud (6) form a comb tooth sealing structure (10), the side wall of the casing (2) is opposite to the impeller (1) and is provided with a plurality of casing water spray openings (7), a drilling spray pipe (3) is formed on the side of the casing (2) facing to one surface of the impeller (1), and a special-shaped exhaust outlet (4) on the casing (2);
the impeller shroud (5) and the casing inner shroud (6) are formed by comb teeth, and comb teeth of the impeller shroud (5) and the casing inner shroud (6) are distributed in a staggered manner to form a labyrinth-shaped comb tooth sealing structure (10);
the main projection shape of the comb teeth is isosceles trapezoid;
four casing water spray openings (7) are arranged, and two adjacent casing water spray openings (7) are 90 degrees apart.
2. The active control method for the tip clearance loss of the single-stage axial flow impulse turbine with partial air intake as claimed in claim 1, wherein the liquid water sprayed out of the water spraying port of the casing (2) resides in the comb seal structure (10) to form a liquid seal film by adjusting the parameters of the comb seal structure (10) formed by the impeller shroud (5) and the casing inner shroud (6) and the parameters of the casing water spraying port (7);
the parameters of the comb tooth sealing structure (10) comprise the number of comb teeth, the height of the comb teeth, the distance between tooth teeth, the width of tooth tops and the included angle between tooth tops of the impeller shroud (5) and the inner shroud (6) of the casing;
the parameters of the casing water jet (7) 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.
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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 true CN114934813B (en) | 2023-12-01 |
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| JPS5560608A (en) * | 1978-10-27 | 1980-05-07 | Hitachi Ltd | Water seal structure for sealing top end portion of rotor blade |
| JP2003269397A (en) * | 2002-03-19 | 2003-09-25 | Ishikawajima Harima Heavy Ind Co Ltd | Chip clearance control device of compressor |
| EP1728973A1 (en) * | 2005-06-01 | 2006-12-06 | Siemens Aktiengesellschaft | Method to block a clearance in a Turbomachine and Turbomachine to carry out the method |
| CN101316999A (en) * | 2005-09-29 | 2008-12-03 | 原动力国际有限责任公司 | Hydrogen g-cycle rotary internal combustion engine |
| CN101153545A (en) * | 2006-09-29 | 2008-04-02 | 通用电气公司 | Stationary-rotating assemblies having surface features for enhanced containment of fluid flow, and related processes |
| CN102733865A (en) * | 2011-03-29 | 2012-10-17 | 阿尔斯通技术有限公司 | Film riding seal for turbines |
| CN103195512A (en) * | 2013-04-24 | 2013-07-10 | 杨开林 | Radial air turbine powered by vacuum suction |
| CN104632296A (en) * | 2013-11-08 | 2015-05-20 | 三菱日立电力系统株式会社 | Axial turbine |
| CN203835470U (en) * | 2014-05-21 | 2014-09-17 | 南京博沃科技发展有限公司 | Blade type sealing device with clearance control function |
| CN105134306A (en) * | 2015-09-18 | 2015-12-09 | 西安交通大学 | Radial rim sealing structure with damping holes and flow guide blades |
| CN105840549A (en) * | 2016-03-30 | 2016-08-10 | 中国科学院工程热物理研究所 | Mechanism for active control over blade top gap and case shape of air compressor within full working condition range |
| CN111630251A (en) * | 2018-01-26 | 2020-09-04 | 第四节股份公司 | Turbine provided with a fluid seal |
| CN112696236A (en) * | 2020-11-10 | 2021-04-23 | 苏州西热节能环保技术有限公司 | Sealing structure based on circumferential relative speed |
| CN113883095A (en) * | 2021-11-02 | 2022-01-04 | 北京航空航天大学 | Casing and fluid power equipment |
| CN114151142A (en) * | 2021-11-11 | 2022-03-08 | 中国联合重型燃气轮机技术有限公司 | Seal assembly and gas turbine |
| CN114396324A (en) * | 2021-12-27 | 2022-04-26 | 哈尔滨工程大学 | Shrouded blade with casing having cooling channel-groove seal-bendable sealing strip composite structure |
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| CN114934813A (en) | 2022-08-23 |
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