CN113969806A - High-power multistage axial flow turbine expander - Google Patents
High-power multistage axial flow turbine expander Download PDFInfo
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- CN113969806A CN113969806A CN202111268017.1A CN202111268017A CN113969806A CN 113969806 A CN113969806 A CN 113969806A CN 202111268017 A CN202111268017 A CN 202111268017A CN 113969806 A CN113969806 A CN 113969806A
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- turbine
- nozzle ring
- bearing box
- axial flow
- cylinder body
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- 238000007789 sealing Methods 0.000 claims description 34
- 238000000926 separation method Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010248 power generation Methods 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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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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
-
- 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
- F01D9/047—Nozzle boxes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to the technical field of expanders, in particular to a high-power multistage axial flow turbine expander; the nozzle ring is fixedly connected with the nozzle ring seat, and is located the inside wall of nozzle ring seat, one side of nozzle ring seat encloses with the inside wall of cylinder body and closes and form the air inlet channel, the opposite side of nozzle ring seat encloses with the inside wall of turbine chamber and closes and form the exhaust runner, the nozzle ring forms turbine stage runner with the turbine, the input and the air inlet channel of turbine stage runner are linked together, the output and the exhaust runner of turbine stage runner are linked together, bearing box and cylinder body fixed connection, and be located the cylinder body, improve expander seal reliability through the setting of above-mentioned structure, solve current cantilever rotor system design difficulty, and simultaneously, reduce the air current loss of expander, and the efficiency is improved.
Description
Technical Field
The invention relates to the technical field of expanders, in particular to a high-power multistage axial flow turbine expander.
Background
In the organic Rankine cycle power generation technology, the efficiency of an organic working medium expander has a large influence on the system efficiency, and the system efficiency can be greatly improved by improving the efficiency of the expander.
At present, in an ORC system, an organic working medium expansion machine is used as core equipment of the ORC system, the requirements on the sealing performance and the stability of a rotor system are very high, the existing high-power expansion machine adopts a simply supported beam type structure, the structure has more than two dynamic sealing points, the sealing reliability is low, and the assembly is complex. And the high-power axial-flow turbine expander adopting the traditional cantilever type structure has the defects of longer cantilever end shaft system, larger mass, difficult design of a rotor system and poorer reinstallation. Meanwhile, the existing expansion machine has large airflow loss, difficult efficiency improvement and poor economical efficiency.
Disclosure of Invention
The invention aims to provide a high-power multistage axial flow turbine expander, which aims to improve the sealing reliability of the expander, solve the design difficulty of the existing cantilever rotor system, reduce the air flow loss of the expander and improve the efficiency.
In order to achieve the above object, the present invention provides a high power multi-stage axial flow turbo expander, which comprises a cylinder, a turbine chamber, a turbine, a nozzle ring seat, a nozzle ring, a bearing box, a main shaft, a front bearing and a rear bearing, wherein the turbine chamber is fixedly connected to the cylinder, the turbine is arranged in the turbine chamber, the bearing box is fixedly connected to the cylinder, the nozzle ring seat is arranged in the cylinder, the nozzle ring seat is fixedly connected to the nozzle ring seat and located on an inner sidewall of the nozzle ring seat, one side of the nozzle ring seat and the inner sidewall of the cylinder enclose an air inlet channel, the other side of the nozzle ring seat and the inner sidewall of the turbine chamber enclose an exhaust channel, the nozzle ring and the turbine form a turbine stage channel, and an input end of the turbine stage channel is communicated with the air inlet channel, the output end of the turbine stage flow passage is communicated with the exhaust flow passage, the bearing box is fixedly connected with the cylinder body and is positioned in the cylinder body, the front bearing and the rear bearing are respectively arranged in the bearing box, and the front bearing and the rear bearing jointly support the main shaft.
The bearing box comprises a front bearing box and a rear bearing box, the front bearing box is fixedly connected with the cylinder body, and the rear bearing box is fixedly connected with the cylinder body and is positioned on one side of the front bearing box.
The turbine comprises a wheel disc and blades, the wheel disc is fixedly connected with the main shaft, the main shaft penetrates through the wheel disc, the wheel disc is provided with multiple stages of blades, and the wheel disc is provided with a plurality of uniformly distributed balance air holes.
The high-power multistage axial-flow turbo expander further comprises a balance air seal, and the balance air seal is arranged between an inner ring surface of the air inlet side of the wheel disc and the rear bearing box.
The high-power multistage axial-flow turbine expander further comprises a sealing body, the sealing body is arranged in the rear bearing box, and the sealing body and one side of the turbine share one section of axial space.
The high-power multistage axial-flow turbine expander further comprises sealing comb teeth, the sealing comb teeth are arranged at the tops of the blades, and labyrinth air seals are formed by the sealing comb teeth and the annular surface of the nozzle annular seat.
The turbine stage runner is a full-circle air inlet type runner.
Wherein the turbine is an axial flow turbine.
The invention relates to a high-power multistage axial flow turbine expander, which enables a sealing body and one side of a turbine to share one section of axial space through a turbine structure, shortens the length of a cantilever shaft system, solves the design difficulty of a cantilever rotor system of the high-power expander, improves the dimensional precision among multistage turbines, reduces the pressure of the medium side of the sealing body and improves the sealing reliability of the sealing body, the gas inlet channel adopts a symmetrical type equal-annular flow channel, and adopts full-circumference gas inlet, so that gas passing through the turbine stage channel does not turn after entering the gas outlet channel and is directly exhausted along the gas outlet channel in the axial direction, the turbine stage channel adopts a full-circumference gas inlet channel, and according to the flow characteristics of the gas, the full-circumference gas inlet mode can enable the gas to be uniformly distributed along the circumferences of a nozzle ring and the turbine without additional separation loss and secondary flow loss, the gas flow enters the turbine stage flow channel from the gas inlet flow channel, and after work is done in the turbine, the gas does not turn to enter the exhaust flow channel, and the gas does not turn to uniformly exhaust along the axial direction, so that the exhaust resistance is reduced, and the working efficiency is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural view of a high-power multistage axial flow turboexpander of the present invention.
Fig. 2 is a schematic view of the structure of the turbine of the present invention.
FIG. 3 is a schematic structural view of a nozzle ring seat and nozzle ring of the present invention.
The device comprises a cylinder body 1, a turbine chamber 2, a turbine 3, a nozzle ring seat 4, a nozzle ring 5, a bearing box 6, a main shaft 7, a front bearing 8, a rear bearing 9, a balance gas seal 10, a sealing body 11, sealing comb teeth 12, a first adjusting block 13, a second adjusting block 14, a guide ring 15, a wheel disc 31, blades 32, a front bearing box 61, a rear bearing box 62, an air inlet channel 101, an air exhaust channel 102 and a turbine stage channel 103.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. 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.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Referring to fig. 1 to 3, the present invention provides a high power multistage axial flow turbine 3 expander, which includes a cylinder 1, a turbine chamber 2, a turbine 3, a nozzle ring seat 4, a nozzle ring 5, a bearing box 6, a main shaft 7, a front bearing 8 and a rear bearing 9, wherein the turbine chamber 2 is fixedly connected to the cylinder 1, the turbine 3 is disposed in the turbine chamber 2, the bearing box 6 is fixedly connected to the cylinder 1, the nozzle ring seat 4 is disposed in the cylinder 1, the nozzle ring 5 is fixedly connected to the nozzle ring seat 4 and is located on an inner sidewall of the nozzle ring seat 4, one side of the nozzle ring seat 4 and the inner sidewall of the cylinder 1 form an inlet flow passage 101, the other side of the nozzle ring seat 4 and the inner sidewall of the turbine chamber 2 form an exhaust flow passage 102, the nozzle ring 5 and the turbine 3 form a turbine stage flow passage 103, the input end of the turbine stage runner 103 is communicated with the intake runner 101, the output end of the turbine stage runner 103 is communicated with the exhaust runner 102, the bearing box 6 is fixedly connected with the cylinder 1 and is located in the cylinder 1, the front bearing 8 and the rear bearing 9 are respectively arranged in the bearing box 6, and the front bearing 8 and the rear bearing 9 jointly support the main shaft 7.
In this embodiment, the intake runner 101 adopts a symmetrical equal-circulation flow channel, and the full-circulation intake mode allows the gas passing through the turbine stage runner 103 to enter the exhaust runner 102 without turning and directly exhaust along the axial direction of the exhaust runner 102, and the turbine stage runner 103 adopts a full-circulation intake mode runner, so that the gas flow can be uniformly distributed along the circumferences of the nozzle ring 5 and the turbine 3 for intake without extra separation loss and secondary flow loss according to the flow characteristics of the gas, and the gas flow enters the turbine stage runner 103 from the intake runner 101, and after the power is applied in the turbine 3, the gas does not turn and enters the exhaust runner 102, and the gas does not turn and uniformly exhausts along the axial direction, thereby reducing the exhaust resistance and improving the working efficiency.
Further, the bearing box 6 includes a front bearing box 61 and a rear bearing box 62, the front bearing box 61 is fixedly connected with the cylinder block 1, and the rear bearing box 62 is fixedly connected with the cylinder block 1 and is located at one side of the front bearing box 61.
In the present embodiment, the front bearing 8 is located in the front bearing housing 61, the rear bearing 9 is located in the rear bearing housing 62, and the front bearing 8 and the rear bearing 9 support the main shaft 7 together.
Further, the turbine 3 includes a wheel disc 31 and blades 32, the wheel disc 31 is fixedly connected with the main shaft 7, the main shaft 7 penetrates through the wheel disc 31, the wheel disc 31 is provided with multiple stages of the blades 32, and the wheel disc 31 is provided with a plurality of uniformly distributed balance air holes.
In this embodiment, 2 ~ 6 rows of blades 32 can be installed to rim plate 31, the hub department on the rim plate 31 is processed there is the end tooth, the end tooth with the end tooth on the main shaft 7 closely meshes, realizes the biography and turns round, simultaneously, it possesses better centering nature and detachability, just each is listed as multistage on the rim plate 31 leave sufficient axial space between the blade 32, ensure multistage blade 32 with there is 2 ~ 5 millimeters axial clearance between the nozzle ring 5.
Further, the high-power multistage axial-flow turbo expander further comprises a balance gas seal 10, and the balance gas seal 10 is arranged between an inner ring surface of the air inlet side of the wheel disc 31 and the rear bearing box 62.
Further, the high-power multistage axial-flow turbo expander further comprises a sealing body 11, the sealing body 11 is arranged in the rear bearing box 62, and the sealing body 11 and one side of the turbine 3 share one section of axial space.
Further, the high-power multistage axial flow turbo expander further comprises sealing comb teeth 12, the sealing comb teeth 12 are arranged at the tops of the blades 32, and labyrinth air seals are formed between the sealing comb teeth 12 and the annular surface of the nozzle annular seat 4.
Further, the turbine stage runner is a full-circle air inlet type runner.
Further, the turbine is an axial flow turbine.
In this embodiment, the radial clearance fit is adopted between the sealing comb teeth 12 and the nozzle ring seat 4 to form a labyrinth air seal, so as to reduce the leakage of the working medium steam non-flow passage, the clearance is controlled to be 0.2-0.5 mm, the radial clearance fit is adopted between the inner ring surface of the rim on the wheel disc 31 and the balance air seal 10 to form the labyrinth air seal, and meanwhile, the balance air seal 10 is communicated with the two sides of the wheel disc 31, so that a sealing cavity defined by the sealing body 11, the rear bearing box 62, the balance air seal 10 and the wheel disc 31 forms a passage with the exhaust low-pressure side, and the passage and the labyrinth air seal formed by the balance air seal 10 act together, so that the pressure on the medium side of the sealing body 11 is reduced, and the sealing reliability of the sealing body 11 is improved.
Further, the high-power multistage axial flow turbo expander further comprises three first adjusting blocks 13 and three second adjusting blocks 14, each second adjusting block 14 is respectively embedded in the nozzle ring seat 4, and the outer side wall of each second adjusting block 14 is provided with the first adjusting block 13.
In the present embodiment, the nozzle ring 5 is supported by three adjustable points, the second adjusting block 14 is disposed in each point, and the radial position of the nozzle ring 5 can be adjusted by adjusting the first adjusting block 13 and the second adjusting block 14, thereby achieving high coaxiality.
Further, the high-power multistage axial flow turboexpander further comprises a guide ring 15, and the guide ring 15 is fixedly connected with the turbine chamber 2 and is located on the inner side wall of the turbine chamber 2.
In the present embodiment, the guide ring 15 having a cone-barrel shape is disposed in the turbine chamber 2, and can guide the exhaust gas of the final turbine 3, so as to avoid the formation of turbulent flow at the end and improve the efficiency.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. A high-power multistage axial-flow turbine expander is characterized in that,
the high-power multistage axial flow turbine expander comprises a cylinder body, a turbine chamber, a turbine, a nozzle ring seat, a nozzle ring, a bearing box, a main shaft, a front bearing and a rear bearing, wherein the turbine chamber is fixedly connected with the cylinder body, the turbine is arranged in the turbine chamber, the bearing box is fixedly connected with the cylinder body, the nozzle ring seat is arranged in the cylinder body, the nozzle ring is fixedly connected with the nozzle ring seat and is positioned on the inner side wall of the nozzle ring seat, one side of the nozzle ring seat and the inner side wall of the cylinder body are enclosed to form an air inlet channel, the other side of the nozzle ring seat and the inner side wall of the turbine chamber are enclosed to form an exhaust channel, the nozzle ring and the turbine form a turbine stage channel, the input end of the turbine stage channel is communicated with the air inlet channel, and the output end of the turbine stage channel is communicated with the exhaust channel, the bearing box is fixedly connected with the cylinder body and is positioned in the cylinder body, the front bearing and the rear bearing are respectively arranged in the bearing box, and the front bearing and the rear bearing jointly support the main shaft.
2. The high power multistage axial flow turboexpander according to claim 1,
the bearing box comprises a front bearing box and a rear bearing box, the front bearing box is fixedly connected with the cylinder body, and the rear bearing box is fixedly connected with the cylinder body and is positioned on one side of the front bearing box.
3. The high power multistage axial flow turboexpander according to claim 2,
the turbine comprises a wheel disc and blades, the wheel disc is fixedly connected with the main shaft, the main shaft penetrates through the wheel disc, the wheel disc is provided with multiple stages of blades, and the wheel disc is provided with a plurality of uniformly distributed balance air holes.
4. The high power multistage axial flow turboexpander according to claim 3,
the high-power multistage axial-flow turbo expander further comprises a balance air seal, and the balance air seal is arranged between an inner ring surface of the air inlet side of the wheel disc and the rear bearing box.
5. The high power multistage axial flow turboexpander according to claim 4,
the high-power multistage axial flow turbine expander further comprises a sealing body, wherein the sealing body is arranged in the rear bearing box, and the sealing body and one side of the turbine share one section of axial space.
6. The high power multistage axial flow turboexpander according to claim 5,
the high-power multistage axial flow turbine expander further comprises sealing comb teeth, the sealing comb teeth are arranged at the tops of the blades, and the sealing comb teeth and the annular surface of the nozzle annular seat form a labyrinth air seal.
7. The high power multistage axial flow turboexpander according to claim 1,
the turbine stage runner is a full-cycle air inlet type runner.
8. The high power multistage axial flow turboexpander according to claim 1,
the turbine is an axial flow turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111268017.1A CN113969806B (en) | 2021-10-29 | 2021-10-29 | High-power multistage axial-flow turboexpander |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111268017.1A CN113969806B (en) | 2021-10-29 | 2021-10-29 | High-power multistage axial-flow turboexpander |
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| Publication Number | Publication Date |
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| CN113969806A true CN113969806A (en) | 2022-01-25 |
| CN113969806B CN113969806B (en) | 2024-02-02 |
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| CN202111268017.1A Active CN113969806B (en) | 2021-10-29 | 2021-10-29 | High-power multistage axial-flow turboexpander |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114961886A (en) * | 2022-04-26 | 2022-08-30 | 天津大学 | Turbo expander and thermal cycle system comprising same |
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Cited By (1)
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|---|---|---|---|---|
| CN114961886A (en) * | 2022-04-26 | 2022-08-30 | 天津大学 | Turbo expander and thermal cycle system comprising same |
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| CN113969806B (en) | 2024-02-02 |
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