CN111305910B - Combined turbine structure with hollow nozzle blades - Google Patents
Combined turbine structure with hollow nozzle blades Download PDFInfo
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- CN111305910B CN111305910B CN202010098600.1A CN202010098600A CN111305910B CN 111305910 B CN111305910 B CN 111305910B CN 202010098600 A CN202010098600 A CN 202010098600A CN 111305910 B CN111305910 B CN 111305910B
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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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
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a combined turbine structure with hollow nozzle blades, which comprises at least one centripetal turbine and at least one stage of axial flow turbine arranged at the downstream of the centripetal turbine, wherein the nozzle blades of the centripetal turbine are of a hollow structure, high-pressure air flow firstly enters the centripetal turbine to do work after passing through a regulating valve arranged in an air inlet channel of an air cylinder, and the exhaust of an impeller is further turned to pass through an axial air flow channel of the nozzle blades to enter the downstream turbine to continue to do work. The invention adopts the centripetal impeller at the first stage, can meet the design requirements of small volume flow and large enthalpy drop, quickly reduce the temperature and pressure of the working medium, and easily realize the full-circumference air intake of the nozzle or improve the partial air intake degree of the nozzle so as to improve the pneumatic efficiency of the turbine and reduce the air flow excitation force borne by the impeller; in addition, when gas at the outlet of the centripetal turbine passes through the axial gas flow channel, the gas can cool the nozzle blades, the requirement on high temperature resistance of blade materials is reduced, and the service life of the blades is prolonged.
Description
Technical Field
The invention belongs to the technical field of turbomachinery, and relates to a combined turbine structure, in particular to a combined turbine structure with hollow nozzle blades, which can meet the design requirements of small volume flow and large enthalpy drop by adopting a centripetal impeller at the first stage, quickly reduce the temperature and pressure of a working medium, easily realize the full-circumference air intake of a nozzle or improve the partial air intake degree of the nozzle, so as to improve the pneumatic efficiency of a turbine and reduce the air flow excitation force borne by the impeller; in addition, when centripetal impeller export gas passes through the hollow part of nozzle vane again, can cool off this blade, reduce the requirement to blade material high temperature resistance, promote the life of blade. Therefore, for the technical requirements of small volume flow and high air inlet temperature, the structure can obviously improve the efficiency, the structural compactness and the operational reliability of the unit, and is suitable for various units such as a steam turbine, a compressed air energy storage expansion machine, a supercritical carbon dioxide expansion machine, a gas turbine, an aircraft engine, an organic working medium turbine and the like.
Background
The turboexpander set is widely applied in the fields of energy and power, and the applicable working medium types, pressure, temperature, rotating speed, power, blade stage number and other design parameters are different.
Firstly, for a turbine set with high inlet pressure and high temperature, the inlet volume flow of the first expansion stage is generally small, if the first stage adopts an axial-flow impeller structure, the height of the blade is small, which will result in large energy loss and low aerodynamic efficiency, and a designer generally adopts a partial air inlet structure scheme to increase the height of the blade of the first stage, but the partial air inlet structure will cause the first stage movable blade to be subjected to strong exciting force generated by periodic airflow at the outlet of the nozzle, which brings great challenges to the design of the structure, strength and service life of the first stage movable blade. In the application field of steam turbines, the first expansion stage is often called as a regulation stage, and the conditions of blade vibration and blade breakage often occur during operation, so that the safety and reliability of a unit are seriously influenced.
In addition, the steam turbine for thermal power generation is developing towards the direction of higher inlet temperature (above 620 ℃) and pressure (above 31 MPa) at present to further improve system efficiency and reduce coal consumption, so that higher requirements are put forward on a cooling structure and blade materials of a first expansion stage, medium and low temperature steam is often additionally introduced into a first-stage nozzle blade for cooling, and the high temperature steam at the inlet does not damage the nozzle blade or reduce the service life of the blade.
Disclosure of Invention
Aiming at the current situations and the defects existing in the prior art, the invention provides a combined turbine structure with a hollow nozzle blade, the first stage adopts a centripetal impeller, the design requirements of small volume flow and large enthalpy drop can be met, the temperature and the pressure of a working medium are quickly reduced, the full-circumference air intake of the nozzle or the partial air intake degree of the nozzle is easily realized, the pneumatic efficiency of the turbine is improved, and the air flow exciting force borne by the impeller is reduced. Therefore, for the technical requirements of small volume flow and high inlet air temperature, the combined turbine structure with the hollow nozzle blades can obviously improve the efficiency, the structural compactness and the operation reliability of the unit, and is suitable for various units such as a steam turbine, a compressed air energy storage expander, a supercritical carbon dioxide expander, a gas turbine, an aircraft engine, an organic working medium turbine and the like.
In order to achieve the technical purpose, the solution of the invention is as follows:
a combined turbine structure with hollow nozzle blades comprises a cylinder, a main shaft, at least one stage of centripetal turbine and at least one stage of axial flow turbine arranged at the downstream of the centripetal turbine, wherein the cylinder comprises a cylinder air inlet channel and a cylinder air outlet channel, the main shaft is arranged at the center of the cylinder, the centripetal turbine and the axial flow turbine are both fixedly arranged on the main shaft, and the combined turbine structure is characterized in that,
the cylinder is further fixedly provided with a centripetal impeller nozzle ring which is arranged along the axial direction, the centripetal impeller nozzle ring is concentrically sleeved on the radial periphery of the centripetal turbine and comprises a front baffle, a rear baffle and a plurality of nozzle blades which are positioned between the front baffle and the rear baffle and are uniformly distributed along the circumferential direction, the space between every two adjacent nozzle blades is formed into a radial airflow channel, the air inlet of each radial airflow channel is just opposite to the annular air outlet of the air inlet passage of the cylinder, and the air outlet of each radial airflow channel is just opposite to the air inlet of the centripetal turbine,
each nozzle blade is a hollow structure with two open ends in the axial direction, air vents matched with the open shapes are arranged on the parts, facing the hollow structures, of the front baffle and the rear baffle, each hollow structure and the air vents arranged at the two ends of the hollow structure form an axial air flow channel,
the cylinder is also provided with a baffling channel, the air inlet of the baffling channel is over against the exhaust port of the centripetal turbine, the air outlet of the baffling channel is over against each axial airflow channel of the nozzle ring of the centripetal impeller, and the air inlet direction and the exhaust direction of the baffling channel are opposite in the axial direction.
In the combined turbine structure with the hollow nozzle blades, high-pressure airflow is introduced through the air inlet channel of the air cylinder, the high-pressure airflow enters the centripetal turbine to expand and do work after passing through each radial airflow channel on the nozzle ring of the centripetal impeller, and exhaust of the centripetal turbine is deflected and reversed in the deflection channel of the air cylinder and then enters each axial airflow channel on the nozzle ring of the centripetal impeller, and then enters each stage of downstream axial flow turbine to continue to do work.
In the combined turbine structure with the hollow nozzle blades, each nozzle blade in the nozzle ring of the centripetal impeller is a hollow structure with openings at two ends, a radial airflow channel between every two adjacent nozzle blades is used for accelerating airflow, turning and pushing the centripetal turbine to do work, and the axial hollow part of each nozzle blade, namely the axial airflow channel, is used for enabling the gas at the outlet of the centripetal turbine to pass through and enter the next stage of turbine to continue to do work. In addition, the hollow portion of each nozzle vane may be used to cool the vane so that the high temperature gas does not damage the nozzle vane or reduce the life of the vane.
In the combined turbine structure with the hollow nozzle blades, the wall thickness of the solid part of each nozzle blade in the centripetal impeller nozzle ring is determined by calculation according to the strength, the rigidity and the thermal stress; the sum of the cross sectional areas of the axial airflow channels formed by the hollow parts of the nozzle vanes is larger than or equal to the outlet area of the centripetal turbine, so that the airflow can not generate obvious pressure loss due to throttling effect when passing through the hollow axial airflow channels of the nozzle vanes; the flow passage area of the front and the rear of the hollow axial airflow passage of the blade and the hollow passage area of the blade are in smooth transition, and the maximum contraction before the passage or expansion angle after the passage does not exceed 45 degrees so as to avoid generating an obvious backflow area. If the strength, rigidity, or hollow flow area of the nozzle vane is insufficient, the outer diameter of the nozzle vane may be increased (i.e., the size of the solid and hollow portions of the vane is increased).
In the combined turbine structure with the hollow nozzle blades, if the nozzle blades in the centripetal impeller nozzle ring are made into an integral or upper and lower semi-combined structure, a suspension pin and a bottom key can be adopted for positioning, centering and rotation prevention; if a single vane assembly is used, it is mounted directly to the block or spacer sleeve spigot.
In the combined turbine structure with the hollow nozzle blades, the maximum outer diameter of the centripetal turbine is determined by stage enthalpy drop, rotor speed and strength/material. The higher the linear velocity of the blade tip, the greater the enthalpy drop of the stage and the lower the outlet temperature and pressure of the centripetal turbine.
In the combined turbine structure with the hollow nozzle blade, the centripetal turbine can be arranged on a main shaft through a hot sleeve/cold sleeve, can also be connected with the main shaft through a flat key, a pull rod/a locking nut, a long screw rod/nut, end face teeth and a spline to transmit mechanical power, and can also be directly milled on a block forged rotor to form an impeller flow channel.
In the combined turbine structure with the hollow nozzle blades, the centripetal turbine can be a closed structure with a wheel cover or an open impeller without the wheel cover, the back of the impeller can be provided with an arc groove for reducing weight, and the combined turbine structure is determined according to strength stress and structural design requirements.
In the combined turbine structure with the hollow nozzle blades, the centripetal turbine can ensure that relative slipping displacement along the axial direction of the main shaft cannot occur in the operation process through the steps, the clamping rings and the clamping sleeve structures on the main shaft.
In the combined turbine structure with the hollow nozzle blades, the impeller of the axial flow turbine can adopt a monobloc forging rotor or a sleeved wheel disc structure.
According to the combined turbine structure with the hollow nozzle blades, the first-stage impeller adopts a centripetal turbine, so that the temperature and the pressure of a working medium can be quickly reduced, the full-circumference air inlet of the nozzle is easy to realize, the pneumatic efficiency is high, and the alternating load borne by the impeller is small; the hollow nozzle blade enables the unit to bear higher air inlet temperature, has good operation reliability, and can replace the existing partial air inlet and axial flow type adjusting stage structure.
Preferably, the combined turbine structure further comprises a diagonal turbine and/or a radial turbine disposed downstream.
Preferably, the centripetal impeller nozzle ring is of an integral structure or an upper-lower half combined structure, and a suspension pin and a bottom key are adopted for positioning, centering and rotation prevention.
Preferably, the centripetal impeller nozzle ring adopts a single nozzle blade piece-by-piece assembly structure, and each nozzle blade is directly arranged on a spigot groove of a cylinder block or a partition plate sleeve.
Preferably, the radial turbine hot or cold housing is on the main shaft, or is connected with the main shaft through flat keys, tie-rods/lock nuts, long screws/nuts, face teeth, and/or splines, or is milled on the block rotor to form the radial turbine.
Preferably, the centripetal turbine is a closed structure with a wheel cover or an open impeller without the wheel cover, and the back of the impeller is provided with an arc groove for reducing weight.
Preferably, the radial inflow turbine carries out axial limiting through a step, a clamping ring and a clamping sleeve structure on the main shaft, and axial relative displacement of the radial inflow turbine along the main shaft due to axial thrust borne by the radial inflow turbine in the operation process is avoided.
Preferably, the combined turbine structure is suitable for various units such as a steam turbine, a compressed air energy storage expander, a supercritical carbon dioxide expander, a helium turbine, a gas turbine, an aircraft engine, an organic working medium turbine, an air separation expander, a steel or chemical industry tail gas turbine, a turbocharger turbine and the like.
Compared with the prior art, the invention has the advantages that:
1. in the combined turbine structure with the hollow nozzle blades, the first stage adopts a centripetal structure, and according to the mechanical principle of an impeller, the single-stage enthalpy drop and the isentropic efficiency of the centripetal turbine under a small volume flow design working condition (or the specific rotating speed is 0.2-1.0) are generally higher than those of an axial flow impeller, so that the full-circumference air inlet structure of the nozzle or the partial air inlet degree of the nozzle can be easily realized, the energy conversion efficiency of the turbine can be improved, the periodic exciting force borne by the first-stage impeller (compared with the partial air inlet structure) is obviously reduced, and the pressure and the temperature of airflow are reduced as soon as possible; in addition, the inherent frequency of the centripetal impeller is generally higher, and the resonance phenomenon is not easy to occur, so that the unit has good operation reliability.
2. In the combined turbine structure with the hollow nozzle blades, each nozzle blade in the centripetal impeller nozzle ring adopts a hollow structure, the gas at the outlet of the first-stage centripetal turbine can roll and enter the next-stage turbine for acting through the hollow part of the nozzle blade, and compared with the existing structure that the gas is firstly changed from the radial direction to the axial direction and then enters the axial flow nozzle after the valve, the combined turbine structure with the hollow nozzle blades is more compact, and the gas inlet of the first-stage nozzle is more uniform.
3. In the combined turbine structure with the hollow nozzle blades, the enthalpy drop of the first-stage centripetal turbine is large, the temperature of airflow at the outlet of the centripetal turbine is obviously reduced, and the blades can be cooled when the airflow passes through the hollow parts of the centripetal nozzle blades after being bent, so that a turbine unit can bear higher inlet air temperature, the requirement on high temperature resistance of blade materials is lowered, the service life of the blades is prolonged, the efficiency and the reliability of the unit can be further improved, and the design difficulty and the cost are lowered.
Drawings
FIG. 1 is a schematic view of a combined turbine with hollow nozzle vanes according to the present invention;
FIG. 2 is an axial cross-sectional view of a centripetal hollow nozzle vane;
FIG. 3 is a partial view of a nozzle ring of the radial impeller;
in the figure, the position of the upper end of the main shaft,
the device comprises a cylinder inlet 1, a cylinder 2, a butterfly valve 3, a centripetal nozzle ring excircle seal 4, a centripetal impeller nozzle ring 5, a centripetal turbine 6, a first-stage axial flow nozzle partition 7, a first-stage axial flow impeller 8, a second-stage axial flow nozzle partition 9, a second-stage axial flow impeller 10, a cylinder exhaust 11, a main shaft 12, a shaft end seal 13, a centripetal impeller outlet wheel cover seal 14, a centripetal nozzle ring inner circle shaft seal 15, an axial flow nozzle partition 16, an axial flow impeller blade top gas seal 17, a centripetal impeller fixing part 18 and a centripetal impeller nozzle blade 19.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The structure and technical scheme of the present invention are further described in detail with reference to the accompanying drawings, and an embodiment of the present invention is provided.
As shown in fig. 1, the combined turbine structure with hollow nozzle blades of the present invention mainly comprises a cylinder inlet 1, a cylinder 2, a butterfly valve 3, a centripetal nozzle ring outer-circle seal 4, a centripetal impeller nozzle ring 5, a centripetal turbine 6, a first-stage axial flow nozzle partition 7, a first-stage axial flow impeller 8, a second-stage axial flow nozzle partition 9, a second-stage axial flow impeller 10, a cylinder exhaust duct 11, a main shaft 12, a shaft end seal 13, a centripetal impeller outlet wheel cover seal 14, a centripetal nozzle ring inner-circle shaft seal 15, an axial flow nozzle partition gas seal 16, an axial flow impeller blade top gas seal 17, and a centripetal impeller fixing member 18 (preferably a snap ring/a ferrule). Specifically, the cylinder 2 includes a cylinder intake passage 1 and a cylinder exhaust passage 11, and a butterfly valve 3 is provided in the cylinder intake passage 1. The main shaft 12 is arranged in the center of the cylinder 2, the centripetal turbine 6, the first-stage axial flow turbine and the second-stage axial flow turbine are evenly and fixedly arranged on the main shaft, and the first-stage axial flow turbine and the second-stage axial flow turbine respectively comprise a first-stage axial flow impeller 8, a second-stage axial flow impeller 10 and a first-stage axial flow nozzle partition plate 7, a second-stage axial flow nozzle partition plate 9 arranged on the upstream of the first-stage axial flow impeller 8, the second-stage axial flow impeller 10. The cylinder 2 is further fixedly provided with a centripetal impeller nozzle ring 5 which is arranged along the axial direction, the centripetal impeller nozzle ring 5 is concentrically sleeved on the radial periphery of the centripetal turbine 6, the centripetal impeller nozzle ring 5 comprises a front baffle plate, a rear baffle plate and a plurality of nozzle blades 19 (shown in figure 2) which are positioned between the front baffle plate and the rear baffle plate and are uniformly distributed along the circumferential direction, the space between every two adjacent nozzle blades 19 forms a radial airflow channel, the air inlet of each radial airflow channel is over against the annular air outlet of the air inlet channel 1 of the cylinder, and the air outlet of each radial airflow channel is over against the air inlet of the centripetal turbine 6; each nozzle blade 19 is a hollow structure with two open ends in the axial direction, air vents matched with the open shapes are arranged on the parts of the front baffle plate and the rear baffle plate, which are opposite to each hollow structure, and each hollow structure and the air vents arranged at the two ends of the hollow structure form an axial air flow channel; the cylinder 2 is also provided with a baffling channel, the air inlet of the baffling channel is opposite to the air outlet of the centripetal turbine 6, the air outlet of the baffling channel is opposite to each axial airflow channel of the centripetal impeller nozzle ring 5, and the air inlet direction and the air outlet direction of the baffling channel are opposite in the axial direction.
When the combined turbine structure with the hollow nozzle blades works, high-pressure and high-temperature gas enters a nozzle ring 5 of a centripetal impeller after passing through an air inlet of an air inlet channel of a cylinder and a butterfly valve 3, and then sequentially enters the centripetal turbine 6 and a first and a second axial-flow impellers 8 and 10 to do work through expansion; the centripetal turbine 6 is sleeved on a main shaft 12, mechanical work is transmitted to the main shaft 12 through a flat key, axial flow blades in the first and second axial flow type impellers 8 and 10 are directly installed on an axial flow impeller disc of a block forged rotor, namely the axial flow blades in the first and second axial flow type impellers 8 and 10 are installed on the axial flow impeller disc of the block forged rotor of the main shaft 12; the centripetal impeller nozzle ring 5 is arranged on the cylinder 2; and gas leakage between the cylinder 2 and the main shaft 12 is reduced through a shaft end seal 13. The gas leakage is reduced by the front and back axial flow type nozzle clapboards 7 and 9 through the axial flow type nozzle clapboard gas seals 16; the centripetal impeller 4 is a closed impeller with a cover, and an outlet cover excircle seal 14 is used for reducing the blade top leakage of the centripetal impeller 6; the axial flow impeller tip gas seal 17 is used to reduce tip leakage flow of the first and second axial flow impellers 8, 10.
Fig. 2 is an axial cross-sectional view of a nozzle ring 5 of a centripetal impeller, wherein each nozzle vane 19 is of a hollow structure, radial airflow channels between each nozzle vane 19 are used for accelerating and deflecting airflow to push the centripetal turbine 6 to do work, the axial airflow channels formed by the hollow parts of each nozzle vane are used for enabling the outlet airflow of the centripetal turbine 6 to pass through and enter the next expansion stage to do work continuously, and the sum of the areas of the hollow parts of each nozzle vane 19 is larger than or equal to the outlet area of the centripetal turbine, so that no obvious throttling effect exists when the airflow passes through.
FIG. 3 is a partial view of a nozzle ring of the centripetal impeller, wherein an outer circumferential seal 4 of the centripetal nozzle ring is mainly composed of hard sharp teeth and J-shaped gas seal teeth which are staggered, and the gap between the sharp teeth is as small as possible, so that gas can be effectively prevented from directly leaking to the front of an axial flow nozzle partition 7 after an air inlet regulating valve; the centripetal impeller nozzle ring 5 is arranged on the cylinder 2 through a spigot, a suspension pin and a bottom key and is used for adjusting the concentricity; comb seals are designed at the positions of the nozzle ring 5 of the centripetal impeller corresponding to the wheel back of the centripetal turbine 6 so as to reduce the leakage flow of the wheel back of the centripetal turbine 6.
The centripetal turbine 6 is axially limited through a step, a clamping ring and an L-shaped clamping sleeve structure on the main shaft 12, and the centripetal impeller is ensured not to axially and relatively displace along the main shaft 12 due to the axial thrust borne by the centripetal impeller in the operation process.
After the high-pressure gas expands in the centripetal impeller 6, the pressure and the temperature are reduced, the volume flow is increased, the second-stage axial-flow impeller is also suitable for full-circle air intake, the height of the blade is large, the high pneumatic efficiency can be achieved, the alternating load borne by the blade is small, and the influence on the service life of the blade is small.
The object of the present invention is fully effectively achieved by the above embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications within the spirit and scope of the appended claims.
Claims (12)
1. A combined turbine structure with hollow nozzle blades comprises a cylinder, a main shaft, at least one stage of centripetal turbine and at least one stage of axial flow turbine arranged at the downstream of the centripetal turbine, wherein the cylinder comprises a cylinder air inlet channel and a cylinder air outlet channel, the main shaft is arranged at the center of the cylinder, the centripetal turbine and the axial flow turbine are respectively and fixedly arranged on the main shaft, the combined turbine structure is characterized in that,
the cylinder is further fixedly provided with a centripetal impeller nozzle ring which is arranged along the axial direction, the centripetal impeller nozzle ring is concentrically sleeved on the radial periphery of the centripetal turbine and comprises a front baffle, a rear baffle and a plurality of nozzle blades which are positioned between the front baffle and the rear baffle and are uniformly distributed along the circumferential direction, the space between every two adjacent nozzle blades is formed into a radial airflow channel, the air inlet of each radial airflow channel is just opposite to the annular air outlet of the air inlet passage of the cylinder, and the air outlet of each radial airflow channel is just opposite to the air inlet of the centripetal turbine,
each nozzle blade is a hollow structure with two open ends in the axial direction, air vents matched with the open shapes are arranged on the parts, facing the hollow structures, of the front baffle and the rear baffle, each hollow structure and the air vents arranged at the two ends of the hollow structure form an axial air flow channel,
the cylinder is also provided with a baffling channel, the air inlet of the baffling channel is over against the exhaust port of the centripetal turbine, the air outlet of the baffling channel is over against each axial airflow channel of the nozzle ring of the centripetal impeller, and the air inlet direction and the exhaust direction of the baffling channel are opposite in the axial direction.
2. The combined turbine structure of claim 1, wherein: the unitized turbine structure further includes a downstream diagonal turbine and/or a radial turbine.
3. The combined turbine structure of claim 1, wherein: the centripetal impeller nozzle ring is of an integral structure or an upper half and a lower half combined structure, and is positioned, centered and prevented from rotating by adopting a suspension pin and a bottom key.
4. The combined turbine structure of claim 1, wherein: the centripetal impeller nozzle ring adopts a structure that single nozzle blades are assembled one by one, and each nozzle blade is directly arranged on a spigot groove of a cylinder body or a partition plate sleeve.
5. The combined turbine structure of claim 1, wherein: the centripetal turbine is sleeved on the main shaft in a hot or cold mode, or the centripetal turbine is milled on the block forged rotor.
6. The combined turbine structure of claim 1, wherein: the centripetal turbine is a closed structure with a wheel cover or an open impeller without the wheel cover, and the back of the impeller is provided with an arc groove for reducing weight.
7. The combined turbine structure of claim 1, wherein: the centripetal turbine carries out axial spacing through step, snap ring, cutting ferrule structure on the main shaft, guarantees that the centripetal turbine can not take place axial relative displacement along the main shaft because of the axial thrust that its received in the operation process.
8. The combined turbine structure of claim 1, wherein: and a regulating valve for controlling air flow is also arranged in the air inlet passage of the air cylinder.
9. The combined turbine structure of claim 1, wherein: and the assembly positions of the front baffle plate and the rear baffle plate of the centripetal impeller nozzle ring and the cylinder are provided with excircle seals.
10. The combined turbine structure of claim 1, wherein: and a shaft end seal is arranged between the cylinder and the main shaft to reduce gas leakage.
11. The combined turbine structure of claim 1, wherein: the centripetal turbine is a closed impeller with a wheel cover, and an outer circle seal is arranged between an outlet wheel cover of the centripetal turbine and the cylinder to reduce the blade top leakage of the centripetal turbine.
12. The combined turbine structure of claim 1, wherein: in the centripetal impeller nozzle ring, the sum of the cross sectional areas of the axial airflow channels formed by the hollow parts of the nozzle blades is larger than or equal to the area of the exhaust port of the deflection channel, so that the airflow can not generate obvious pressure loss due to throttling effect when passing through the axial airflow channels.
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| CN113074022B (en) * | 2021-04-12 | 2022-06-14 | 北京理工大学 | Centripetal turbine using axial flow guide vanes |
| CN114776403B (en) * | 2021-12-29 | 2023-12-26 | 东方电气集团东方汽轮机有限公司 | Air inlet structure and method suitable for large enthalpy drop small flow turbine |
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| NL99624C (en) * | 1955-08-29 | |||
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| CN201190583Y (en) * | 2008-04-30 | 2009-02-04 | 冀江 | Combined turbo-expander |
| CN102094705A (en) * | 2011-02-22 | 2011-06-15 | 孙敏超 | Turbine nozzle ring with adjustable and variable outlet flowing angle |
| CN103306736B (en) * | 2012-04-30 | 2015-10-14 | 王政玉 | A kind of power turbine and power engine thereof |
| CN107457358B (en) * | 2017-08-24 | 2018-12-14 | 西安中工动力能源有限公司 | The casting method of miniature gas turbine turbine rotor |
| CN109779698A (en) * | 2019-01-29 | 2019-05-21 | 东方电气集团东方汽轮机有限公司 | A kind of turbine structure that single-shaft multi-stage runoff-axis stream combines |
| CN209761504U (en) * | 2019-03-11 | 2019-12-10 | 贵州黎阳天翔科技有限公司 | Rotor assembly structure for micro gas turbine |
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2020
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