CN109083704B - Thermal insulation and heat dissipation device and method for supercritical working medium turbine set shell - Google Patents
Thermal insulation and heat dissipation device and method for supercritical working medium turbine set shell Download PDFInfo
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- CN109083704B CN109083704B CN201811119268.1A CN201811119268A CN109083704B CN 109083704 B CN109083704 B CN 109083704B CN 201811119268 A CN201811119268 A CN 201811119268A CN 109083704 B CN109083704 B CN 109083704B
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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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Thermal Insulation (AREA)
Abstract
The invention discloses a heat-insulating and radiating device and a heat-insulating and radiating method for a supercritical working medium turbine set shell, wherein the heat-insulating and radiating device comprises a block-type combined heat-insulating and radiating shell, an inlet pipeline and an outlet pipeline of the heat-insulating and radiating shell, ribs, a turbine body, a turbine base, a main shaft support, a connecting edge, an inlet and an outlet of the turbine body. The invention has the advantages of low cost and high operability.
Description
Technical Field
The invention relates to the technical field of heat preservation and radiation of supercritical working medium turbine set shells, in particular to a heat preservation and radiation device and method of a supercritical working medium turbine set shell.
Background
In a supercritical carbon dioxide brayton cycle or alam cycle system, the temperature of the design regime is typically between 600 and 1300 ℃ and the design pressure is between 20 and 32 MPa. For the advanced circulating system with high design parameters, the energy density of the turbine set is extremely high, so that the design service life of the turbine set is longer than 20 years, the design thickness value of the shell of the turbine set body is larger than that of the traditional turbine set, the heat storage capacity of the turbine set body is extremely large, the heat of the shell of the turbine set is difficult to dissipate in the emergency shutdown process, and if the heat of the shell cannot be dissipated for a long time, the structure of a dry gas sealed stator part in the shell can be damaged. Meanwhile, the turbine body needs to be insulated under the design working condition of the turbine, so that the heat loss of the system to the environment can be reduced, and the thermal efficiency of the operation working condition of the system is improved. This presents a problem: how to realize the supercritical working medium turbine group shell body in the starting process, the design working condition and the working condition changing process and normal shutdown process, the shell body is insulated, and the heat dissipation of the shell body is quickened in the emergency shutdown process of the accident working condition. At present, no technical scheme is available for not only insulating the supercritical working medium turbine group shell, but also promoting the heat dissipation of the shell in case of an emergency.
Disclosure of Invention
The invention aims to solve the problems and provide a heat-insulating and radiating device and a heat-insulating and radiating method for a supercritical working medium turbine set shell, which are characterized in that a heat-insulating shell with a block-assembled structure is designed and covered on the outer side of a turbine set body with an inlet and outlet pipeline, so that the turbine set body can be insulated in a normal working state, meanwhile, the heat-insulating shell is enabled to be separated from the turbine set body by a certain gap, and low-temperature air sent by a fan enters the gap between the heat-insulating shell and the turbine set body during an emergency working condition to take away heat of the turbine set body, so that the turbine set body can be rapidly radiated under the emergency working condition.
The invention realizes the above purpose through the following technical scheme:
the supercritical working medium turbine group shell heat-insulating and radiating device comprises a block type combined heat-insulating and radiating shell 1, one or more heat-insulating and radiating shell inlet pipelines 2 and one or more heat-insulating and radiating shell outlet pipelines 3 which are communicated with the inside and the outside of the block type combined heat-insulating and radiating shell 1, ribs 4 arranged on the inner surface of the block type combined heat-insulating and radiating shell 1, a turbine body 5 arranged in the block type combined heat-insulating and radiating shell 1, a main shaft support 7 for supporting two ends of the turbine body 5, a turbine base 6 for fixing the main shaft support 7, a turbine body inlet 9 and a turbine body outlet 10 arranged on the turbine body 5, wherein the block type combined heat-insulating and radiating shell 1 consists of a plurality of heat-insulating and radiating shell modules; the modules of the block type combined heat-preserving and heat-radiating shell 1 are connected with the block type combined heat-preserving and heat-radiating shell 1, the main shaft support 7 and the turbine base 6 through the connecting edge 8.
The block type combined heat-insulating and heat-radiating shell 1 comprises a right lower plate-shaped heat-insulating and heat-radiating shell module 1A, a right upper arc-shaped heat-insulating and heat-radiating shell module 1B, a left arc-shaped flat plate-shaped heat-insulating and heat-radiating shell module 1C, an arc trapezoid-shaped heat-insulating and heat-radiating shell module 1D and a heat-insulating layer 1E arranged on the inner surfaces of the four heat-insulating and heat-radiating shell modules which are sequentially connected, wherein the arc trapezoid-shaped heat-insulating and heat-radiating shell module 1D consists of a right lower arc trapezoid-shaped heat-insulating and heat-radiating shell module 1D-1 and a left lower arc trapezoid-shaped heat-insulating and heat-radiating shell module 1D-2; the outer shape of the right lower plate-shaped heat-insulating heat-radiating shell module 1A, the right upper arc-shaped heat-insulating heat-radiating shell module 1B, the left arc-shaped flat plate-shaped heat-insulating heat-radiating shell module 1C, the right lower arc trapezoid-shaped heat-insulating heat-radiating shell module 1D-1 and the left lower arc trapezoid-shaped heat-insulating heat-radiating shell module 1D-2 after being connected is matched with the outer shape of the turbine body 5.
The connecting edge 8 comprises a support connecting edge 8A and a module connecting edge 8B, the block type combined heat-preserving and heat-radiating shell 1 is connected with the main shaft support 7 through the support connecting edge 8A, and the block type combined heat-preserving and heat-radiating shell 1 is fixedly connected between the modules and the turbine base 6 through the module connecting edge 8B.
The heat-insulating and heat-radiating shell modules of the block-type combined heat-insulating and heat-radiating shell 1 are provided with holes or half-holes, and the sizes, namely the radiuses or the inner diameters, of the heat-insulating and heat-radiating shell modules are matched with the outer diameters of the turbine body inlet 9 or the turbine body outlet 10, so that the turbine body inlet 9 or the turbine body outlet 10 can pass through the heat-insulating and heat-radiating shell modules; gaps are formed between the inner wall surfaces of the four heat-insulating and heat-radiating shell modules of the block type combined heat-insulating and heat-radiating shell 1 and the outer wall surface of the turbine body 5.
The heat-insulating and heat-radiating shell inlet pipeline 2 and the heat-insulating and heat-radiating shell outlet pipeline 3 of the block-type combined heat-insulating and heat-radiating shell 1 are positioned on different blocks of the block-type combined heat-insulating and heat-radiating shell 1 or on the same block-type combined heat-insulating and heat-radiating shell 1.
The rib 4 is fixed on the inner surface of any sub-module of the block type combined heat insulation and radiation shell 1 near the outer surface side of the turbine body 5, the shape of the rib 4 is linear or annular or spiral or screw thread or sectional turning, and the thickness of the rib 4 is equal thickness or monotonically increasing thickness or monotonically decreasing thickness or non-monotonically increasing/decreasing thickness distribution.
According to the control method of the supercritical working medium turbine group shell heat-preserving and heat-radiating device, when the machine is started, normally works or is stopped, the pressure in the supercritical working medium turbine group shell heat-preserving and heat-radiating device is basically equal to the outside, an inlet pipeline 2 of the heat-preserving and heat-radiating shell and an outlet pipeline 3 of the heat-preserving and heat-radiating shell are in a closed state, the gas between the block type combined heat-preserving and heat-radiating shell 1 and the turbine body 5 is in a stable state, and the supercritical working medium turbine group shell heat-preserving and heat-radiating device is used for preserving the turbine group; when in emergency working conditions, the control system sends out a command to open the heat-preserving and heat-radiating shell inlet pipeline 2 and the heat-preserving and heat-radiating shell outlet pipeline 3, air is supplied to the heat-preserving and heat-radiating shell inlet pipeline 2 through the fan, the air passes through gaps between the plurality of modules of the block type combined heat-preserving and heat-radiating shell 1 with the fins 4 and the turbine body 5, heat in the shell of the turbine body 5 is taken away rapidly, and the supercritical working medium turbine set shell heat-preserving and heat-radiating device radiates a turbine set rapidly.
The invention has the beneficial effects that:
at present, no reliable solution is known for solving the problems of the supercritical carbon dioxide Brayton cycle or Allam cycle system, which can not only insulate the supercritical working medium turbine group shell, but also promote the heat dissipation of the shell in case of emergency. The invention provides a heat-insulating and radiating device and a heat-insulating and radiating method for a supercritical working medium turbine set shell with low manufacturing cost and high operability.
Drawings
FIG. 1 is a schematic diagram of a thermal insulation heat dissipation device for a supercritical working fluid turboset housing of the present invention.
1 is a block type combined heat-insulating and radiating shell, wherein 1A is a lower right plate-shaped heat-insulating and radiating shell module, 1B is an upper right arc-shaped heat-insulating and radiating shell module, 1C is a left arc-shaped flat plate-shaped heat-insulating and radiating shell module, 1D is an arc trapezoid-shaped heat-insulating and radiating shell module, 1D-1 is a lower right arc trapezoid-shaped heat-insulating and radiating shell module, 1D-2 is a lower left arc trapezoid-shaped heat-insulating and radiating shell module, and 1E is a heat-insulating layer; 2 is an inlet pipeline of the heat-preserving heat-dissipating shell; 3 is an outlet pipeline of the heat-preserving heat-dissipating shell; 4 is a rib; 5 is a turbine body; 6 is a turbine base; 7 is a main shaft support; 8 is a connecting edge, wherein 8A is a support connecting edge, and 8B is a module connecting edge; 9 is the inlet of the turbine body; 10 is the turbine body outlet.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
as shown in fig. 1, the supercritical working medium turbine group shell heat-insulating and heat-radiating device comprises a block type combined heat-insulating and heat-radiating shell 1, one or more heat-insulating and heat-radiating shell inlet pipelines 2 and one or more heat-insulating and heat-radiating shell outlet pipelines 3 which are communicated with the inside and outside of the block type combined heat-radiating shell 1, ribs 4 arranged on the inner surface of the block type combined heat-radiating shell 1, a turbine body 5 arranged in the block type combined heat-radiating shell 1, a main shaft support 7 for supporting two ends of the turbine body 5, a turbine base 6 for fixing the main shaft support 7, a turbine body inlet 9 and a turbine body outlet 10 arranged on the turbine body 5, wherein the block type combined heat-insulating and heat-radiating shell 1 consists of a plurality of heat-insulating and heat-radiating shell modules; the modules of the block type combined heat-preserving and heat-radiating shell 1 are connected with the block type combined heat-preserving and heat-radiating shell 1, the main shaft support 7 and the turbine base 6 through the connecting edge 8.
As shown in fig. 1, as a preferred embodiment of the present invention, the block-type combined heat-insulating and heat-dissipating shell 1 includes a lower right plate-shaped heat-insulating and heat-dissipating shell module 1A, an upper right circular arc-shaped heat-insulating and heat-dissipating shell module 1B, a left circular arc-shaped flat plate-shaped heat-insulating and heat-dissipating shell module 1C, a circular arc trapezoid-shaped heat-insulating and heat-dissipating shell module 1D, and a heat-insulating layer 1E provided on the inner surfaces of the four heat-insulating and heat-dissipating shell modules, wherein the circular arc trapezoid-shaped heat-insulating and heat-dissipating shell module 1D is composed of a lower right circular arc trapezoid-shaped heat-insulating and heat-dissipating shell module 1D-1 and a lower left circular arc trapezoid-shaped heat-insulating and heat-dissipating shell module 1D-2; the outer shape of the right lower plate-shaped heat-insulating heat-radiating shell module 1A, the right upper arc-shaped heat-insulating heat-radiating shell module 1B, the left arc-shaped flat plate-shaped heat-insulating heat-radiating shell module 1C, the right lower arc trapezoid-shaped heat-insulating heat-radiating shell module 1D-1 and the left lower arc trapezoid-shaped heat-insulating heat-radiating shell module 1D-2 after being connected is matched with the outer shape of the turbine body 5.
As shown in fig. 1, as a preferred embodiment of the present invention, the connection edge 8 includes a support connection edge 8A and a module connection edge 8B, the block-type combined heat-insulating and heat-dissipating housing 1 is connected to the spindle support 7 through the support connection edge 8A, and the block-type combined heat-insulating and heat-dissipating housing 1 modules are connected and fixed to the turbine base 6 through the module connection edge 8B.
The heat-insulating and heat-radiating shell modules of the block-type combined heat-insulating and heat-radiating shell 1 are provided with holes or half-holes, and the sizes, namely the radiuses or the inner diameters, of the heat-insulating and heat-radiating shell modules are matched with the outer diameters of the turbine body inlet 9 or the turbine body outlet 10, so that the turbine body inlet 9 or the turbine body outlet 10 can pass through the heat-insulating and heat-radiating shell modules; gaps are formed between the inner wall surfaces of the four heat-insulating and heat-radiating shell modules of the block type combined heat-insulating and heat-radiating shell 1 and the outer wall surface of the turbine body 5.
The heat-insulating and heat-radiating shell inlet pipeline 2 and the heat-insulating and heat-radiating shell outlet pipeline 3 of the block-type combined heat-insulating and heat-radiating shell 1 are positioned on different blocks of the block-type combined heat-insulating and heat-radiating shell 1 or on the same block-type combined heat-insulating and heat-radiating shell 1.
As a preferred embodiment of the invention, the rib 4 is fixed on the inner surface of the submodule of any block type combined heat-preserving and heat-radiating shell 1 near the outer surface side of the turbine body 5, the shape of the rib 4 is linear or annular or spiral or screw thread or sectional turning type, and the thickness of the rib 4 is equal thickness or monotonically increasing thickness or monotonically decreasing thickness or non monotonically increasing/decreasing thickness distribution form.
The control method of the heat preservation and heat dissipation device of the supercritical working medium turbine group shell comprises the following steps:
when in operation, the control method of the heat preservation and heat dissipation device of the supercritical working medium turbine group shell is specifically expressed as follows: when the machine is started, normally works or stops, the pressure in the heat-preserving and radiating device of the supercritical working medium turbine set shell is basically equal to the outside, the inlet pipeline 2 of the heat-preserving and radiating shell and the outlet pipeline 3 of the heat-preserving and radiating shell are in a closed state, the gas between the block type combined heat-preserving and radiating shell 1 and the turbine body 5 is in a stable state, and the heat-preserving and radiating device of the supercritical working medium turbine set shell is used for preserving the heat of the turbine set; when in emergency working conditions, the control system sends out a command to open the heat-preserving and heat-radiating shell inlet pipeline 2 and the heat-preserving and heat-radiating shell outlet pipeline 3, air is supplied to the heat-preserving and heat-radiating shell inlet pipeline 2 through the fan, the air passes through gaps between the plurality of modules of the block type combined heat-preserving and heat-radiating shell 1 with the fins 4 and the turbine body 5, heat in the shell of the turbine body 5 is taken away rapidly, and the supercritical working medium turbine set shell heat-preserving and heat-radiating device radiates a turbine set rapidly.
The technical scheme of the invention is not limited to the specific embodiment, and all technical modifications made according to the technical scheme of the invention fall within the protection scope of the invention.
Claims (3)
1. The heat preservation and heat dissipation device for the supercritical working medium turbine group shell is characterized in that: the heat-insulating and heat-radiating combined type heat-radiating device comprises a block-type combined heat-insulating and heat-radiating shell (1), one or more heat-insulating and heat-radiating shell inlet pipelines (2) and one or more heat-insulating and heat-radiating shell outlet pipelines (3) which are communicated with the inside and outside of the block-type combined heat-radiating shell (1), ribs (4) arranged on the inner surface of the block-type combined heat-insulating and heat-radiating shell (1), a turbine body (5) arranged in the block-type combined heat-insulating and heat-radiating shell (1), main shaft supports (7) for supporting two ends of the turbine body (5), a turbine base (6) for fixing the main shaft supports (7), a turbine body inlet (9) and a turbine body outlet (10) are arranged on the turbine body (5), and the block-type combined heat-insulating and heat-radiating shell (1) is composed of a plurality of heat-insulating and heat-radiating shell modules; the modules of the block type combined heat-insulating and radiating shell (1) and the block type combined heat-insulating and radiating shell (1) are connected with the main shaft support (7) and the turbine base (6) through connecting edges (8);
gaps are formed between the inner wall surfaces of the four heat-insulating heat-radiating shell modules of the block type combined heat-insulating heat-radiating shell (1) and the outer wall surface of the turbine body (5);
the rib (4) is fixed on the inner surface of a submodule of any block type combined heat-preserving and heat-radiating shell (1) close to the outer surface side of the turbine body (5), the shape of the rib (4) is linear or annular, spiral or threaded or sectional turning, and the thickness of the rib (4) is equal thickness or monotonically increasing thickness or monotonically decreasing thickness or non-monotonically increasing/decreasing variable thickness distribution form;
the block type combined heat-insulating and heat-radiating shell (1) comprises a right lower plate-shaped heat-insulating and heat-radiating shell module (1A), a right upper arc-shaped heat-insulating and heat-radiating shell module (1B), a left arc-shaped flat plate-shaped heat-insulating and heat-radiating shell module (1C), an arc trapezoid-shaped heat-insulating and heat-radiating shell module (1D) and heat-insulating layers (1E) arranged on the inner surfaces of the four heat-insulating and heat-radiating shell modules, wherein the arc trapezoid-shaped heat-insulating and heat-radiating shell module (1D) consists of a right lower arc trapezoid-shaped heat-insulating and heat-radiating shell module (1D-1) and a left lower arc trapezoid-shaped heat-insulating and heat-radiating shell module (1D-2); the outer shape of the right lower plate-shaped heat-insulating and radiating shell module (1A), the right upper arc-shaped heat-insulating and radiating shell module (1B), the left arc-shaped flat plate-shaped heat-insulating and radiating shell module (1C), the right lower arc trapezoid-shaped heat-insulating and radiating shell module (1D-1) and the left lower arc trapezoid-shaped heat-insulating and radiating shell module (1D-2) are matched with the outer shape of the turbine body (5);
the connecting edge (8) comprises a support connecting edge (8A) and a module connecting edge (8B), the block type combined heat-insulating and heat-radiating shell (1) is connected with the main shaft support (7) through the support connecting edge (8A), and the block type combined heat-insulating and heat-radiating shell (1) modules are fixedly connected with the turbine base (6) through the module connecting edge (8B);
the heat-insulating and heat-radiating shell modules of the block type combined heat-insulating and heat-radiating shell (1) are provided with holes or half-hole structures, and the holes or half-hole structures are matched with the outer diameter of the turbine body inlet (9) or the turbine body outlet (10), so that the turbine body inlet (9) or the turbine body outlet (10) can penetrate through the heat-insulating and heat-radiating shell modules.
2. The supercritical working fluid turbine group shell heat preservation and radiation device according to claim 1, wherein: the heat-insulating and heat-radiating shell inlet pipeline (2) and the heat-insulating and heat-radiating shell outlet pipeline (3) of the block-type combined heat-insulating and heat-radiating shell (1) are positioned on different blocks of the block-type combined heat-insulating and heat-radiating shell (1) or on the same block-type combined heat-insulating and heat-radiating shell (1).
3. The control method of the supercritical working substance turbine group shell heat preservation and radiation device as set forth in claim 1 or 2, characterized in that: when the machine is started, normally works or stops, the pressure in the heat-insulating and radiating device of the supercritical working medium turbine group shell is basically equal to the outside, the inlet pipeline (2) of the heat-insulating and radiating shell and the outlet pipeline (3) of the heat-insulating and radiating shell are in a closed state, the gas between the block type combined heat-insulating and radiating shell (1) and the turbine body (5) is in a stable state, and the heat-insulating and radiating device of the supercritical working medium turbine group shell is used for insulating the turbine group; when the emergency working condition is met, the control system sends out a command to open the heat-preserving and heat-radiating shell inlet pipeline (2) and the heat-preserving and heat-radiating shell outlet pipeline (3), the fan supplies air for the heat-preserving and heat-radiating shell inlet pipeline (2), the air passes through gaps between the plurality of modules of the block type combined heat-preserving and heat-radiating shell (1) with the fins (4) and the turbine body (5), heat in the shell of the turbine body (5) is taken away rapidly, and the supercritical working medium turbine group shell heat-preserving and heat-radiating device radiates a turbine group rapidly.
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| CN201811119268.1A CN109083704B (en) | 2018-09-25 | 2018-09-25 | Thermal insulation and heat dissipation device and method for supercritical working medium turbine set shell |
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| CN201811119268.1A CN109083704B (en) | 2018-09-25 | 2018-09-25 | Thermal insulation and heat dissipation device and method for supercritical working medium turbine set shell |
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| CN109083704B true CN109083704B (en) | 2023-10-20 |
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| CN114087038A (en) * | 2021-11-11 | 2022-02-25 | 重庆江增船舶重工有限公司 | Cooling structure and method for cylinder body during shutdown of supercritical carbon dioxide turbine |
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| CN109083704A (en) | 2018-12-25 |
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