CN108999660A - Composite cooling apparatus and its working method inside and outside overcritical working medium turbine heat preservation and external impact type - Google Patents
Composite cooling apparatus and its working method inside and outside overcritical working medium turbine heat preservation and external impact type Download PDFInfo
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- CN108999660A CN108999660A CN201811114417.5A CN201811114417A CN108999660A CN 108999660 A CN108999660 A CN 108999660A CN 201811114417 A CN201811114417 A CN 201811114417A CN 108999660 A CN108999660 A CN 108999660A
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- 238000001816 cooling Methods 0.000 title claims abstract description 50
- 238000004321 preservation Methods 0.000 title claims abstract description 29
- 239000002131 composite material Substances 0.000 title claims abstract description 23
- 238000000034 method Methods 0.000 title claims abstract description 12
- 230000008676 import Effects 0.000 claims description 11
- 230000007423 decrease Effects 0.000 claims description 6
- 230000003116 impacting effect Effects 0.000 claims description 4
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 4
- 230000003247 decreasing effect Effects 0.000 claims description 3
- 230000003121 nonmonotonic effect Effects 0.000 claims description 3
- 230000001788 irregular Effects 0.000 claims description 2
- 238000009738 saturating Methods 0.000 claims 1
- 238000009423 ventilation Methods 0.000 abstract description 3
- 230000007306 turnover Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 7
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 3
- 229910002092 carbon dioxide Inorganic materials 0.000 description 2
- 239000001569 carbon dioxide Substances 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000013003 hot bending Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
Classifications
-
- 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
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
- F01K7/32—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines using steam of critical or overcritical pressure
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention discloses composite cooling apparatus and its working methods inside and outside the heat preservation of overcritical working medium turbine and external impact type, the device includes turbine ontology, main shaft, spindle bearing, support plate, insulating layer, impact shell, impact chamber, impact opening, outer cold intake and exhaust pipeline, interior cold and outer cold ventilating fan, mainstream intake and exhaust pipeline, interior cold intake and exhaust branch, valve, it may be implemented in non-accident conditions and turbine ontology kept the temperature by insulating layer, pass through the valve of closing mainstream turnover pipeline in accident conditions, open the valve of outer cold intake and exhaust pipeline and interior cold intake and exhaust branch, a part of cooling air is sent into impact shell by blower, external impact cooling is carried out to turbine ontology, the chamber that another part cooling air is sent into turbine ontology is cooled down on the inside of turbine ontology, it realizes from the inside and outside of turbine ontology while taking away heat Amount, the present invention is cooling using impinging cooling structure cooperation inner ventilation, and the cooling time of overcritical working medium turbine ontology accident conditions can be made shorter.
Description
Technical field
The present invention relates to the heat preservation of overcritical working medium turbine set shell and cooling technology fields, and in particular to a kind of overcritical
Composite cooling apparatus and its working method inside and outside the heat preservation of working medium turbine and external impact type.
Background technique
In supercritical carbon dioxide Brayton cycle or the Allam circulatory system, the temperature of design conditions usually 600 to
Between 1300 DEG C, design pressure is 20 between 32MPa.For the advanced circulatory system of above-mentioned high design parameter, turbine set
Energy density is high, for guarantee turbine set projected life at 20 years or more, the design thickness value of the shell of turbine set ontology
Thickness than traditional Steam Turbine is big, and the amount of stored heat of turbine set ontology is very huge, makes turbine set in emergency shutdown process
The heat of middle shell is difficult to disperse, if shell long-time heat cannot disperse, can not only extend the repair time of unit, can also
The dry gas seals stator part structure in shell is damaged, the rate of breakdown that the deformation of rotor main shaft hot bending occurs is also increased.
Meanwhile needing to keep the temperature turbine set ontology in turbine accidental conditions, the heat of system can be reduced to environment
It scatters and disappears, improves the system conditions thermal efficiency.It thus brings a problem: how to realize overcritical working medium turbine set shell
In start-up course, design conditions and varying load process, orderly closedown process, shell is kept the temperature, is promptly stopped in accident conditions
Accelerate shell heat dissipation during machine.Currently, there is no technical solution overcritical working medium turbine set shell can be kept the temperature and
It is able to achieve in emergency episode and promotes shell heat dissipation.
Summary of the invention
The object of the invention is that providing a kind of overcritical working medium turbine heat preservation and external to solve the above-mentioned problems
Composite cooling apparatus and its working method inside and outside impingement, the present invention is cooling using impinging cooling structure cooperation inner ventilation, can
Keep the cooling time of overcritical working medium turbine ontology accident conditions shorter.
The present invention through the following technical solutions to achieve the above objectives:
Composite cooling apparatus inside and outside overcritical working medium turbine heat preservation and external impact type, including turbine ontology 1, main shaft 2, master
It is shaft stool 3, support plate 4, insulating layer 5, impact shell 6, impact chamber 7, impact opening 8, outer cold admission line 9, shut-off valve 10, outer cold
Ventilating fan 11, outer cold exhaust pipeline 12, check valve 13, mainstream admission line 14, mainstream air inlet shut-off valve 15, mainstream exhaust pipe
Road 16, mainstream are vented shut-off valve 17, interior cold air inlet branch road 18, interior cold air inlet shut-off valve 19, interior cold ventilating fan 20, interior cold exhaust
Branch 21 and interior cold exhaust shut-off valve 22, wherein main shaft 2 is located at the middle part of turbine ontology 1,2 both ends of main shaft by its two sides main shaft branch
Seat 3 supports, and support plate 4 is fixed on 3 end of spindle bearing of two sides and turbine ontology 1 is disposed within, and insulating layer 5 is fixed on branch
The outside of fagging 4, impact shell 6 are fixed on the inside of support plate 4, impact in the middle part of shell 6 comprising at least one impact chamber 7, punching
It hits the inside torus shape of shell 6 and the axially external anchor ring of turbine ontology 1 is the similar anchor ring in space, impact the interior side ring of shell 6
There are several impact openings 8 on face, the import of each impact opening 8 is connected with impact chamber 7, and the center line of each impact opening 8 extends
Line intersects with the axially external anchor ring of turbine ontology 1, and outer cold admission line 9 is fixed in support plate 4, outer cold admission line 9
Input end is provided with outer cold ventilating fan 11, and the outlet end of outer cold admission line 9 sequentially passes through insulating layer 5 and support plate 4 and punching
The impact chamber 7 hit inside shell 6 is connected, and shut-off valve 10 is arranged on cold admission line 9 outside, and outer cold exhaust pipeline 12 is fixed on
In support plate 4, the space that the import of outer cold exhaust pipeline 12 and support plate 4, turbine pedestal and two spindle bearings 3 are surrounded connects
It is logical, check valve 13 is provided on outer cold exhaust pipeline 12, the outer outlet of cold exhaust pipeline 12 sequentially passes through support plate 4 and insulating layer
5 are connected to workshop ambient atmosphere, and mainstream admission line 14 sequentially passes through insulating layer 5 and support plate 4 and the chamber of turbine ontology 1 connects
It is logical, mainstream air inlet shut-off valve 15, the chamber of mainstream exhaust pipe 16 import and turbine ontology 1 are provided on mainstream admission line 14
Room connection, the outlet of mainstream exhaust pipe 16 sequentially pass through support plate 4 and insulating layer 5 to stretching on the outside of turbine systems, arrange in mainstream
Mainstream exhaust shut-off valve 17 is provided in feed channel 16, one end of interior cold air inlet branch road 18 is connected with mainstream admission line 14,
The tie point of interior cold air inlet branch road 18 and mainstream admission line 14 between mainstream air inlet shut-off valve 15 and insulating layer 5, it is interior it is cold into
The other end of gas branch 18 is provided with interior cold ventilating fan 20, and interior cold air inlet shut-off valve 19 is provided in interior cold air inlet branch road 18,
One end of interior cold exhaust branch 21 is connected with mainstream exhaust pipe 16, the connection of interior cold exhaust branch 21 and mainstream exhaust pipe 16
Point is vented between shut-off valve 17 and insulating layer 5 in mainstream, and interior cold exhaust shut-off valve 22 is provided on interior cold exhaust branch 21, interior cold
21 other end of exhaust branch is connected to workshop ambient atmosphere.
External cooling working medium in interior cooling working medium and outer cold admission line 9 in the interior cold air inlet branch road 18 is sky
Gas.
The interior side ring surface of the impact shell 6 is 0.5cm to 2.0cm at a distance from the axially external anchor ring of turbine ontology 1.
The pass of the impact opening 8 is triangle, trapezoidal, regular polygon, irregular polygon, round or ellipse, hole
Center line and 2 center line angulation of main shaft be 20 ° to 90 °, the flow area in hole is steady state value or list from import to outlet
It adjusts and is incremented by or monotone decreasing or be first incremented by successively decreases afterwards or first successively decreases and is incremented by afterwards or non-monotonic form.
The support plate 4, insulating layer 5, impact shell 6, impact chamber 7 are monoblock type or muti-piece combined type.
The pressure loss of the license through-flow direction of the check valve 13 is less than 150Pa.
The working method of composite cooling apparatus can be retouched specifically inside and outside the overcritical working medium turbine heat preservation and external impact type
It states as two working conditions, the first working condition, in non-accident conditions, shut-off valve 10, check valve 13, interior cold air inlet shut-off valve 19
Off state, Compound cooling dress inside and outside overcritical working medium turbine heat preservation and external impact type are in interior cold exhaust shut-off valve 22
Set to turbine ontology 1 carry out heat preservation and it is heat-insulated；Second working condition, in accident conditions, mainstream air inlet shut-off valve 15 and mainstream row
Gas shut-off valve 17 is in close state, and shut-off valve 10, check valve 13, interior cold air inlet shut-off valve 19 and interior cold exhaust shut-off valve 22 are equal
In the open state, a part of outside air enters outer cold admission line 9 and impact shell after boosting by outer cold ventilating fan 11
Body 6 is flowed out to the progress impinging cooling of turbine ontology 1 from impact opening 8 after flowing through impact chamber 7, is then flowed from outer cold exhaust pipeline 12
To the workshop external world, another part outside air boosted by interior cold ventilating fan 20 after into interior cold air inlet branch road 18 and mainstream into
Feed channel 14 flow to workshop by mainstream exhaust pipe 16 and interior cold exhaust branch 21 after the internal chamber of turbine ontology 1
The external world, in this state, composite cooling apparatus carries out fastly turbine ontology 1 inside and outside overcritical working medium turbine heat preservation and external impact type
Quickly cooling is but.
The beneficial effects of the present invention are:
Currently, there is not yet can be used for solving in supercritical carbon dioxide Brayton cycle or the Allam circulatory system, both
Overcritical working medium turbine set shell can be carried out keeping the temperature and there is the reliable of the function of promoting shell heat dissipation in emergency episode
Solution.The invention proposes in a kind of low cost, the operability high heat preservation of overcritical working medium turbine and external impact type
Outer composite cooling apparatus, the support plate that the present invention is fixed on support and turbine pedestal by design, by normal operating conditions
Turbine ontology covers on inside, and insulating layer is arranged on the outside of support plate, may be implemented to carry out turbine ontology in normal operating conditions
Heat preservation, is provided with the impact shell with multiple rows of impact opening with turbine set ontology certain interval, in master on the inside of support plate
Inner cool tube road cooling on the inside of turbine ontology can be entered by, which being provided on flow inlet and outlet pipeline, passes through wind in emergency episode operating condition
A part of Cryogenic air sent is entered the impact chamber of impact shell by machine, is uniformly sent gas to each impact by impact chamber
Hole, gas pass through impact opening high speed impact turbine ontology at a certain angle, quickly take away the heat of turbine ontology, another part is low
Warm air is sent directly into the inner cavity of turbine ontology after pressurizeing by blower, take away turbine ontology heat from inside, two strands of gases are most
Whole road flow on the outside of workshop, by the inside and outside of turbine ontology while taking away the heat of turbine and realize in emergency episode
Operating condition is rapidly cooled turbine set ontology.The present invention is cooling using impinging cooling structure cooperation inner ventilation, can make to surpass
The cooling time of critical working medium turbine ontology accident conditions is shorter.
Detailed description of the invention
Fig. 1 is the schematic diagram of composite cooling apparatus inside and outside the overcritical working medium turbine heat preservation of the present invention and external impact type.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings:
As shown in Figure 1, composite cooling apparatus inside and outside overcritical working medium turbine heat preservation and external impact type, including turbine ontology
1, main shaft 2, spindle bearing 3, support plate 4, insulating layer 5, impact shell 6, impact chamber 7, impact opening 8, outer cold admission line 9, cut
Only valve 10, outer cold ventilating fan 11, outer cold exhaust pipeline 12, check valve 13, mainstream admission line 14, mainstream air inlet shut-off valve
15, mainstream exhaust pipe 16, mainstream are vented shut-off valve 17, interior cold air inlet branch road 18, interior cold air inlet shut-off valve 19, interior cold air inlet wind
Machine 20, interior cold exhaust branch 21 and interior cold exhaust shut-off valve 22, wherein main shaft 2 is located at the middle part of turbine ontology 1,2 both ends of main shaft by
The spindle bearing 3 of two sides supports, and support plate 4 is fixed on 3 end of spindle bearing of two sides and turbine ontology 1 is disposed within, guarantor
Warm layer 5 is fixed on the outside of support plate 4, and impact shell 6 is fixed on the inside of support plate 4, and impacting includes at least one in the middle part of shell 6
A impact chamber 7, inside torus shape and the axially external anchor ring of turbine ontology 1 for impacting shell 6 are the similar anchor ring in space, impact shell
There are several impact openings 8 on the interior side ring surface of body 6, the import of each impact opening 8 is connected with impact chamber 7, each impact opening 8
Center line extended line intersects with the axially external anchor ring of turbine ontology 1, and outer cold admission line 9 is fixed in support plate 4, it is outer it is cold into
The input end of feed channel 9 is provided with outer cold ventilating fan 11, and outer cold admission line 9 sequentially passes through insulating layer 5 and support plate 4, outside
Cold 9 outlet end of admission line is connected with the impact chamber 7 inside impact shell 6, and shut-off valve is arranged on cold admission line 9 outside
10, outer cold exhaust pipeline 12 is fixed in support plate 4, the import of outer cold exhaust pipeline 12 and support plate 4, turbine pedestal and two
The space connection that spindle bearing 3 is surrounded, is provided with check valve 13, outer cold exhaust pipeline 12 is successively on outer cold exhaust pipeline 12
Across support plate 4 and insulating layer 5, the outlet of outer cold exhaust pipeline 12 is connected to workshop ambient atmosphere, mainstream admission line 14 according to
The secondary chamber across insulating layer 5 and support plate 4 and turbine ontology 1, is provided with mainstream air inlet on mainstream admission line 14
Shut-off valve 15, the chamber of mainstream exhaust pipe 16 import and turbine ontology 1, the outlet of mainstream exhaust pipe 16 sequentially pass through branch
Fagging 4 and insulating layer 5 are provided with mainstream exhaust shut-off valve 17 to stretching on the outside of turbine systems on mainstream exhaust pipe 16, interior
One end of cold air inlet branch road 18 is connected with mainstream admission line 14, the connection of interior cold air inlet branch road 18 and mainstream admission line 14
For point between mainstream air inlet shut-off valve 15 and insulating layer 5, the other end of interior cold air inlet branch road 18 is provided with interior cold ventilating fan 20,
Interior cold air inlet shut-off valve 19, one end and 16 phase of mainstream exhaust pipe of interior cold exhaust branch 21 are provided in interior cold air inlet branch road 18
Even, the tie point of interior cold exhaust branch 21 and mainstream exhaust pipe 16 is vented between shut-off valve 17 and insulating layer 5 in mainstream, interior cold
Interior cold exhaust shut-off valve 22 is provided on exhaust branch 21, interior 21 other end of cold exhaust branch is connected to workshop ambient atmosphere.
Interior cooling working medium and outer cold air inlet pipe as the preferred embodiment of the present invention, in the interior cold air inlet branch road 18
External cooling working medium in road 9 is air.The interior side ring surface of the impact shell 6 and the axially external anchor ring of turbine ontology 1
Distance is 0.5cm to 2.0cm.
As the preferred embodiment of the present invention, the pass of the impact opening 8 is triangle, trapezoidal, regular polygon, does not advise
Then polygon, round or ellipse, the center line and 2 center line angulation of main shaft in hole are 20 ° to 90 °, the flow area in hole
It is steady state value or monotonic increase or monotone decreasing from import to outlet or is first incremented by successively decrease afterwards or first successively decrease to be incremented by afterwards or non-monotonic
Form.
As the preferred embodiment of the present invention, the support plate 4, insulating layer 5, impact shell 6, impact chamber 7 are whole
Body formula or muti-piece combined type.
As the preferred embodiment of the present invention, the pressure loss of the license through-flow direction of the check valve 13 is less than
150Pa。
The working method of composite cooling apparatus can be retouched specifically inside and outside the overcritical working medium turbine heat preservation and external impact type
It states as two states, the first working condition, in non-accident conditions, shut-off valve 10, check valve 13, interior cold air inlet shut-off valve 19 and interior
Cold exhaust shut-off valve 22 is in off state, composite cooling apparatus pair inside and outside overcritical working medium turbine heat preservation and external impact type
Turbine ontology 1 carry out heat preservation and it is heat-insulated；Second working condition, in accident conditions, mainstream air inlet shut-off valve 15 and mainstream exhaust are closed
Disconnected valve 17 is in close state, and shut-off valve 10, check valve 13, interior cold air inlet shut-off valve 19 and interior cold exhaust shut-off valve 22 are in
Open state, a part of outside air enter outer cold admission line 9 and impact shell 6 after boosting by outer cold ventilating fan 11,
It is flowed out from impact opening 8 to the progress impinging cooling of turbine ontology 1 after flowing through impact chamber 7, then flow to factory from outer cold exhaust pipeline 12
Room is extraneous, and another part outside air enters interior cold air inlet branch road 18 and mainstream air inlet pipe after boosting by interior cold ventilating fan 20
Road 14 is flow to outside workshop after the internal chamber of turbine ontology 1 by mainstream exhaust pipe 16 and interior cold exhaust branch 21
Boundary, in this state, composite cooling apparatus carries out quickly turbine ontology 1 inside and outside overcritical working medium turbine heat preservation and external impact type
It is cooling.
Claims (7)
1. composite cooling apparatus inside and outside overcritical working medium turbine heat preservation and external impact type, it is characterised in that: including turbine ontology
(1), main shaft (2), spindle bearing (3), support plate (4), insulating layer (5), impact shell (6), impact chamber (7), impact opening (8),
Outer cold admission line (9), shut-off valve (10), outer cold ventilating fan (11), outer cold exhaust pipeline (12), check valve (13), mainstream
Admission line (14), mainstream air inlet shut-off valve (15), mainstream exhaust pipe (16), mainstream are vented shut-off valve (17), interior cold air inlet
Branch (18), interior cold air inlet shut-off valve (19), interior cold ventilating fan (20), interior cold exhaust branch (21) and interior cold exhaust shut-off valve
(22), wherein main shaft (2) is located in the middle part of turbine ontology (1), and main shaft (2) both ends are supported by the spindle bearing (3) of its two sides, support
Plate (4) is fixed on spindle bearing (3) end of two sides and turbine ontology (1) is disposed within, and insulating layer (5) is fixed on support plate
(4) outside, impact shell (6) are fixed on the inside of support plate (4), include at least one impact chamber in the middle part of impact shell (6)
(7), inside torus shape and turbine ontology (1) the axially external anchor ring for impacting shell (6) are the similar anchor ring in space, impact shell
(6) there are several impact openings (8) on interior side ring surface, the import of each impact opening (8) is connected with impact chamber (7), Mei Gechong
The center line extended line for hitting hole (8) intersects with turbine ontology (1) axially external anchor ring, and outer cold admission line (9) is fixed on branch
On fagging (4), the input end of outer cold admission line (9) is provided with outer cold ventilating fan (11), the outlet of outer cold admission line (9)
End sequentially passes through insulating layer (5) and support plate (4) the impact chamber (7) internal with shell (6) are impacted and is connected, outside cold air inlet pipe
Shut-off valve (10) are set on road (9), outer cold exhaust pipeline (12) is fixed on support plate (4), outer cold exhaust pipeline (12) into
The space that mouth is surrounded with support plate (4), turbine pedestal and two spindle bearings (3) is connected to, on outer cold exhaust pipeline (12)
It is provided with check valve (13), outer cold exhaust pipeline (12) outlet sequentially passes through support plate (4) and insulating layer (5) and workshop is extraneous big
Gas connection, mainstream admission line (14) sequentially pass through the chamber of insulating layer (5) and support plate (4) and turbine ontology (1),
It is provided with mainstream air inlet shut-off valve (15) on mainstream admission line (14), (16) import of mainstream exhaust pipe and turbine ontology (1)
Chamber, mainstream exhaust pipe (16) outlet sequentially pass through support plate (4) and insulating layer (5) to turbine systems outside stretch
Out, mainstream exhaust shut-off valve (17), one end of interior cold air inlet branch road (18) and mainstream are provided on mainstream exhaust pipe (16)
Admission line (14) is connected, and the tie point of interior cold air inlet branch road (18) and mainstream admission line (14) is in mainstream air inlet shut-off valve
(15) between insulating layer (5), the other end of interior cold air inlet branch road (18) is provided with interior cold ventilating fan (20), interior cold air inlet branch
Interior cold air inlet shut-off valve (19), one end and mainstream exhaust pipe (16) phase of interior cold exhaust branch (21) are provided on road (18)
Even, the tie point of interior cold exhaust branch (21) and mainstream exhaust pipe (16) is in mainstream exhaust shut-off valve (17) and insulating layer (5)
Between, interior cold exhaust shut-off valve (22), interior cold exhaust branch (21) other end and workshop are provided on interior cold exhaust branch (21)
Ambient atmosphere connection.
2. composite cooling apparatus inside and outside overcritical working medium turbine heat preservation according to claim 1 and external impact type, special
Sign is: the external cooling working medium in the interior cooling working medium and outer cold admission line (9) in the interior cold air inlet branch road (18) is equal
For air.
3. composite cooling apparatus inside and outside overcritical working medium turbine heat preservation according to claim 1 and external impact type, special
Sign is: it is described impact shell (6) interior side ring surface with turbine ontology (1) axially external anchor ring at a distance from be 0.5cm extremely
2.0cm。
4. composite cooling apparatus inside and outside overcritical working medium turbine heat preservation according to claim 1 and external impact type, special
Sign is: the pass of the impact opening (8) is triangle, trapezoidal, regular polygon, irregular polygon, round or ellipse, hole
Center line and main shaft (2) center line angulation be 20 ° to 90 °, the flow area in hole be from import to outlet steady state value or
Monotonic increase or monotone decreasing or be first incremented by successively decreases afterwards or first successively decreases and be incremented by afterwards or non-monotonic form.
5. composite cooling apparatus inside and outside overcritical working medium turbine heat preservation according to claim 1 and external impact type, special
Sign is: the support plate (4), insulating layer (5), impact shell (6), impact chamber (7) are monoblock type or muti-piece combined type.
6. composite cooling apparatus inside and outside overcritical working medium turbine heat preservation according to claim 1 and external impact type, special
Sign is: the pressure loss of the license through-flow direction of the check valve (13) is less than 150Pa.
7. composite cooling apparatus inside and outside overcritical working medium turbine heat preservation as claimed in any one of claims 1 to 6 and external impact type
Working method, it is characterised in that: including two working conditions, the first working condition, in non-accident conditions, shut-off valve (10),
Check valve (13), interior cold air inlet shut-off valve (19) and interior cold exhaust shut-off valve (22) are in off state, and overcritical working medium is saturating
Composite cooling apparatus carries out heat preservation and heat-insulated to turbine ontology (1) inside and outside flat heat preservation and external impact type；Second working condition,
Accident conditions, mainstream air inlet shut-off valve (15) and mainstream exhaust shut-off valve (17) are in close state, shut-off valve (10), check valve
(13), interior cold air inlet shut-off valve (19) and interior cold exhaust shut-off valve (22) are in open state, and a part of outside air passes through
Enter outer cold admission line (9) and impact shell (6) after outer cold ventilating fan (11) boosting, flows through after impacting chamber (7) from impact
Hole (8) outflow carries out impinging cooling to turbine ontology (1), then flow to the workshop external world, another portion from outer cold exhaust pipeline (12)
Divide outside air by entering interior cold air inlet branch road (18) and mainstream admission line (14) after interior cold ventilating fan (20) boosting, wears
After crossing the internal chamber of turbine ontology (1), it is flow to the workshop external world by mainstream exhaust pipe (16) and interior cold exhaust branch (21),
In this state, composite cooling apparatus is carried out turbine ontology (1) quick inside and outside overcritical working medium turbine heat preservation and external impact type
It is cooling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811114417.5A CN108999660B (en) | 2018-09-25 | 2018-09-25 | External impact type internal and external composite cooling and heat preservation device and method for supercritical working medium turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811114417.5A CN108999660B (en) | 2018-09-25 | 2018-09-25 | External impact type internal and external composite cooling and heat preservation device and method for supercritical working medium turbine |
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| Publication Number | Publication Date |
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| CN108999660A true CN108999660A (en) | 2018-12-14 |
| CN108999660B CN108999660B (en) | 2023-12-19 |
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| CN201811114417.5A Active CN108999660B (en) | 2018-09-25 | 2018-09-25 | External impact type internal and external composite cooling and heat preservation device and method for supercritical working medium turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920016A (en) * | 2019-11-30 | 2020-03-27 | 重庆瑞霆塑胶有限公司 | Air cooling system |
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| CN1073502A (en) * | 1991-11-19 | 1993-06-23 | 通用电气公司 | Integrated steam/air cooling system for gas turbines |
| JPH06159008A (en) * | 1992-11-26 | 1994-06-07 | Hitachi Ltd | Monitoring, protection, and performance managing device of steam turbine forced cooling device |
| JPH08114103A (en) * | 1994-10-18 | 1996-05-07 | Toshiba Corp | Casing cooling structure for steam turbine |
| CN106014509A (en) * | 2016-07-28 | 2016-10-12 | 中国核动力研究设计院 | Turbine generator set adopting supercritical carbon dioxide as working medium |
| CN208831049U (en) * | 2018-09-25 | 2019-05-07 | 西安热工研究院有限公司 | Composite cooling apparatus inside and outside overcritical working medium turbine heat preservation and external impact type |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920016A (en) * | 2019-11-30 | 2020-03-27 | 重庆瑞霆塑胶有限公司 | Air cooling system |
| CN110920016B (en) * | 2019-11-30 | 2021-05-28 | 重庆瑞霆塑胶有限公司 | Air cooling system |
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