CN109139122A - A kind of inner cooling system of 2 grades of turbine rotors of gas turbine - Google Patents
A kind of inner cooling system of 2 grades of turbine rotors of gas turbine Download PDFInfo
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- CN109139122A CN109139122A CN201811320228.3A CN201811320228A CN109139122A CN 109139122 A CN109139122 A CN 109139122A CN 201811320228 A CN201811320228 A CN 201811320228A CN 109139122 A CN109139122 A CN 109139122A
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- turbine
- wheel disc
- turbine wheel
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- chamber
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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
- F01D5/08—Heating, heat-insulating or cooling means
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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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A kind of inside cooling structure of 2 grades of turbine rotors of gas turbine, belongs to gas turbine structure field.The present invention is in order to solve the two stage turbine gas turbine rotor structures of existing not coaxial different rotating speeds, without a kind of applicable inside cooling structure problem.The present invention includes cooling air guiding device, first order turbine wheel disc, second level turbine wheel disc, turbine front end axis and turbine rear axle, turbine front end axis is hollow shaft, turbine rear axle is arranged in the axis of turbine front end, turbine front end axis and the concentric arrangement of turbine rear axle, the circumferential direction of turbine front end axis is provided with level-one turbine wheel disc connection ring, the circumferential direction of turbine rear axle is provided with second level turbine wheel disc connection ring, first order turbine wheel disc is fixedly mounted in level-one turbine wheel disc connection ring, and second level turbine wheel disc is fixedly mounted in second level turbine wheel disc connection ring.The present invention maximizes the dosage for reducing high pressure cooling air, improves gas turbine proficiency, realizes the inner cooling system of not coaxial different rotating speeds turbine rotor.
Description
Technical field
The present invention relates to a kind of inner cooling systems of gas turbine, belong to gas turbine structure field.
Background technique
Currently, an effective ways for improving its cycle efficieny are the combustions for improving combustion gas turbine for gas turbine unit
Gas inlet temperature, and improving one effective ways of initial temperature is exactly to pass through reasonable cooling air system to high-temperature component of gas turbine
Design is cooled down and is protected to it, since the temperature that the high-temperature material that current turbine blade uses can bear is restricted,
Therefore to the high-temperature component of gas turbine, especially turbine blade, it is necessary to take reliable cooling provision to reduce its work temperature
Degree, to guarantee the operation of gas turbine safety, improve turbine working-blade cooling effect be development high efficiency combustion engine must
So require.
For gas turbine, the gas turbine cooling system scheme inquired into patent has been delivered at present, both for passing through
The monoblock type that the means such as bolt or welding are bound up coaxially with the turbine rotor of revolving speed the case where, however, for having
Two stage turbine, and the turbine rotor of the gas turbine of the not coaxial different rotating speeds of two stage turbine, there are no in applicable turbine rotor
Portion's cooling system scheme.
Summary of the invention
The purpose of the present invention is to solve existing different rotating speeds two stage turbine gas turbine rotor structures, without a kind of suitable
Inside cooling structure problem, and then a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine is provided.
Technical solution of the present invention:
A kind of inside cooling structure of 2 grades of turbine rotors of gas turbine, including cooling air guiding device, first order turbine
Wheel disc, second level turbine wheel disc, turbine front end axis and turbine rear axle, the turbine front end axis are hollow shaft, turbine rear end
Axis is arranged in the axis of turbine front end, turbine front end axis and the concentric arrangement of turbine rear axle, the circumferential direction of the turbine front end axis
It is provided with level-one turbine wheel disc connection ring, the circumferential direction of the turbine rear axle is provided with second level turbine wheel disc connection ring, and first
Grade turbine wheel disc is fixedly mounted in level-one turbine wheel disc connection ring, and second level turbine wheel disc is fixedly mounted on second level turbine wheel disc
In connection ring；
The cooling air guiding device is used to introduce the cooling air-flow of the gas turbine from compressor exhaust, cooling
Air-deflector and first order turbine wheel disk form blade bottom chamber, before the two forms first order turbine wheel disc with shell again
Chamber, the cooling air-flow from hiigh pressure stage bleed are largely passed through wheel disc rear chamber after flowing through first order turbine wheel disc front chamber,
Small part from first order root of blade is passed through the after converging after blade bottom chamber with the cooling air-flow from compressor exhaust
One grade blade；
It is equipped with stator blade inner ring between the first order turbine wheel disc and second level turbine wheel disc, is equipped in stator blade inner ring
Spacer member, spacer member will be separated to form first order turbine wheel disc rear chamber between first order turbine wheel disc and second level turbine wheel disc
With second level turbine wheel disc front chamber, cooling air-flow flows through first order turbine wheel disc rear chamber and second level turbine wheel disc ante-chamber
Room cools down after cooling respective wheel disc side on rear side of first order root of blade respectively and after cooling second level root of blade again to second
Grade blade gas supply.
Lower chamber between two-stage disk stage, turbine are formed at the first order turbine wheel disc and second level turbine wheel disc lower part
Between centers circulation chamber is formed with turbine rear axle inside the axis of front end, lower chamber connects between centers circulation chamber and two-stage disk stage
It is logical；
The second level turbine wheel disc connection ring that the second level turbine wheel disc and turbine rear axle is circumferentially arranged forms second level
The installation place of turbine wheel disc lower part cooling chamber, the second level turbine wheel disc and second level turbine wheel disc connection ring radially processes
There are multiple first through hole, forms second level turbine wheel disc rear chamber, stream between the second level turbine wheel disc and turbine cylinder body
Through between two-stage disk stage lower chamber cooling air-flow flow into second level turbine wheel disc lower part cooling chamber, and by first through hole into
It is cooled down on rear side of the root of blade of the second level after entering second level turbine wheel disc rear chamber.
Further, the upper end of the cooling air guiding device uses labyrinth gas seals structure and first order turbine wheel disc
Top be coupled, the middle part of the lower part of cooling air guiding device and first order turbine wheel disc uses the first labyrinth seal knot
Structure is coupled, and blade bottom chamber is formed on the top of cooling air guiding device and first order turbine wheel disc；The cooling
The lower case of air-deflector is equipped with gas tight jacket, and gas tight jacket is cooperated using the second comb tooth sealing structure and turbine front end axis
Installation, the gentle big envelope of cooling air guiding device, shell, first order turbine wheel disc form first order turbine wheel disc front chamber.
Further, the lower end for the spacer member installed in the stator blade inner ring uses third comb tooth sealing structure and first
The lower end of grade turbine wheel disc is coupled.
Further, it is close that the 4th comb tooth sealing structure, the 5th comb teeth is respectively adopted in the left and right ends of the stator blade inner ring
Seal structure is coupled with first order turbine wheel disc, second level turbine wheel disc.
Further, the between centers circulation chamber interior that the turbine rear axle and turbine front end axis are formed is equipped with air
Pipe is introduced, between centers circulation chamber is separated to form compressor sub-high pressure grade tap air channel to air introduction and compressor low-pressure stage is drawn
Gas channel is equipped with axle sleeve in the turbine rear axle, by the 6th comb tooth sealing structure between axle sleeve and turbine front end axis,
Axial ring gap is formed between axle sleeve and second level turbine wheel pan bottom, compressor low-pressure stage tap air channel passes through the 6th comb teeth
Lower chamber is connected between sealing structure and two-stage disk stage, meanwhile, compressor low-pressure stage tap air channel passes through axial ring gap
Cooling chamber is connected to second level turbine wheel disc lower part.Further, between the turbine front end axis and first order turbine wheel disc
Level-one turbine wheel pan bottom cooling chamber is formed, is radially machined with multiple second through-holes on the turbine front end axis, it is described
Compressor sub-high pressure grade tap air channel is connected to by the second through-hole with level-one turbine wheel pan bottom cooling chamber, level-one turbine wheel disc
Lower chamber is connected between bottom coohng chamber and two-stage disk stage.
Further, it is machined with multiple third through-holes in the axial direction of the cooling air guiding device, described first
Grade turbine wheel disc top is machined with hole on multiple first order wheel discs, on third through-hole and the first order wheel disc hole respectively with blade bottom
Chamber, the cooling air-flow of compressor exhaust is after the third through-hole of cooling air guiding device enters blade bottom chamber
First order turbine rotor vane root of blade is passed through by hole on first order wheel disc and provides cooling air for first order movable vane；Described
The middle position of level-one turbine wheel disc is machined with multiple fourth holes, and the first order turbine wheel disc front chamber passes through four-way
Hole is connected to first order turbine wheel disc rear chamber.
Further, the top of the second level turbine wheel disc is machined with hole on multiple second level wheel discs, the second step cone
Hole is connected to second level turbine wheel disc front chamber on disk, and the cooling air-flow into second level turbine wheel disc front chamber passes through the second level
Hole is passed through second level turbine rotor vane root of blade and provides cooling air for second level movable vane on wheel disc.
Further, pass through the 7th comb tooth sealing structure cooperation peace between the second level turbine wheel disc and turbine cylinder body
Dress, the cooling air-flow into second level turbine wheel disc rear chamber flow through cooling second level turbine rotor vane after the 7th comb tooth sealing structure
On rear side of root of blade.
Further, the first order turbine wheel disc is connected by screw bolts mode and is fixedly mounted on level-one turbine wheel disc company
It connects on ring, the second level turbine wheel disc is fixedly mounted in second level turbine wheel disc connection ring.
The invention has the following advantages: the present invention draws four bursts of compressed airs as cold from the different parts of compressor
But a part of gas, high-pressure compressor exhaust flows into first order turbine wheel disc blade bottom chamber by air-deflector, main
Cooling air is provided for first order turbine rotor vane；Bleed reaches the first order by the second comb tooth sealing structure between compressor hiigh pressure stage
Turbine wheel disc front chamber, then be passed through by multiple fourth holes in the middle position of first order turbine wheel disc on rear side of wheel disc first
Grade turbine wheel disc rear chamber, main cooling first order turbine wheel disc two sides；Bleed between compressor low-pressure stage passes through turbine front end axis
The compressor low-pressure stage tap air channel of inside center between centers circulation chamber is passed through lower chamber between two-stage disk stage；Compressor time is high
It arbitrarily downgrades a bleed, first order turbine wheel pan bottom is passed through by compressor sub-high pressure grade tap air channel, behind cooling wheel pan bottom, with
Compressor low-pressure stage tap air channel air-flow converges, and provides cooling air jointly for second level turbine wheel disc movable vane and the cooling second level is saturating
Flat wheel disc two sides；Each stock air-flow is ultimately discharged into main blast tube after the cooling each structural plane of journey；
Cooling medium of the invention uses the compressed air drawn from compressor, it then follows the cooling at turbine high temperature and pressure position
Gas is drawn from compressor high-pressure section, and the lower second level turbine wheel sections cooling air of temperature and pressure is mainly from compressor
The principle that the low-pressure stage of front is drawn maximizes the dosage for reducing high pressure cooling air, improves gas turbine proficiency, realizes not
The inner cooling system of coaxial different rotating speeds turbine rotor, this system have cooling turbine rotor component, supply for cooling blade,
The effect for preventing combustion gas from flowing backward and obturaging.
Detailed description of the invention
Fig. 1 is gas turbine turbine rotor inner cooling system flow passage structure diagrammatic cross-section；
1- cooling air guiding device in figure, 2- third through-hole, 3- labyrinth gas seals structure, hole on 4- first order wheel disc, 5-
First order turbine wheel disc, the 4th comb tooth sealing structure of 6-, 7- stator blade inner ring, 8- spacer member, 9- first order turbine wheel disc rear chamber,
The 5th comb tooth sealing structure of 10-, hole on the wheel disc of the second level 11-, the second level 12- turbine wheel disc, the second level 13- turbine wheel disc ante-chamber
Room, the 7th comb tooth sealing structure of 14-, 15- turbine cylinder body, the second level 16- turbine wheel disc rear chamber, 17- first through hole, 18- bis-
Grade turbine wheel disc lower part cooling chamber, 19- third comb tooth sealing structure, 20- turbine rear axle, 21- axial ring gap, 22-
Axle sleeve, the 6th comb tooth sealing structure of 23-, lower chamber between 24- two-stage disk stage, 26- compressor low-pressure stage tap air channel, 27-
Air introduction, 28- compressor sub-high pressure grade tap air channel, 29- turbine front end axis, the second through-hole of 30-, 31- level-one turbine wheel
Pan bottom cooling chamber, the second comb tooth sealing structure of 32-, 33- gas tight jacket, 34- first order turbine wheel disc front chamber, 35- first
Comb tooth sealing structure, 36- blade bottom chamber, 37- fourth hole, 38- level-one turbine wheel disc connection ring, 39- second level turbine wheel
Disk connection ring, 40- between centers circulation chamber, 41- shell.
Specific embodiment
Specific embodiment 1: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
The inside cooling structure of rotor, including cooling air guiding device 1, first order turbine wheel disc 5, second level turbine wheel disc 12, thoroughly
Flat front end axis 29 and turbine rear axle 20, the turbine front end axis 29 are hollow shaft, and turbine rear axle 20 is arranged before turbine
It holds in axis 29, turbine front end axis 29 and the concentric arrangement of turbine rear axle 20, the circumferential direction of the turbine front end axis 29 are provided with
Level-one turbine wheel disc connection ring 38, the circumferential direction of the turbine rear axle 20 are provided with second level turbine wheel disc connection ring 39, and first
Grade turbine wheel disc 5 is fixedly mounted in level-one turbine wheel disc connection ring 38, and it is saturating that second level turbine wheel disc 12 is fixedly mounted on second level
In flat wheel disc connection ring 39；
The cooling air guiding device 1 is used to introduce the cooling air-flow of gas turbine, cooling air guiding device 1 with
First order turbine wheel disc 5 forms blade bottom chamber 36 and first order turbine wheel disc front chamber 34, and cooling air-flow flows through the first order
Cooling first order root of blade after turbine wheel disc front chamber 34 and blade bottom chamber 36；
Stator blade inner ring 7 is equipped between the first order turbine wheel disc 5 and second level turbine wheel disc 12, in stator blade inner ring 7
Spacer member 8 is installed, it is saturating that spacer member 8 will be separated to form the first order between first order turbine wheel disc 5 and second level turbine wheel disc 12
Flat wheel disc rear chamber 9 and second level turbine wheel disc front chamber 13, cooling air-flow flow through first order turbine wheel disc rear chamber 9 and second
Cooling first order root of blade rear side is second with second level root of blade cooling duct is passed through after grade turbine wheel disc front chamber 13
Grade blade provides cooling air；
Lower chamber between two-stage disk stage is formed at the first order turbine wheel disc 5 and 12 lower part of second level turbine wheel disc
24, axis 29 inside in turbine front end forms between centers circulation chamber 40, between centers circulation chamber 40 and two-stage disk stage with turbine rear axle
Between lower chamber 24 be connected to；
39 shape of second level turbine wheel disc connection ring that the second level turbine wheel disc 12 and turbine rear axle 20 is circumferentially arranged
At second level turbine wheel disc lower part cooling chamber 18, the peace of the second level turbine wheel disc 12 and second level turbine wheel disc connection ring 39
It is radially machined with multiple first through hole 17 at dress, forms the second level between the second level turbine wheel disc 12 and turbine cylinder body 15
Turbine wheel disc rear chamber 16 flows through the cooling air-flow inflow second level turbine wheel disc lower part cooling of lower chamber 24 between two-stage disk stage
Chamber 18, and pass through first through hole 17 and enter cooling second level root of blade rear side after second level turbine wheel disc rear chamber 16.Such as
This setting, the inside cooling structure of 2 grades of turbine rotors of gas turbine is the combustion gas formed by cylinder body and two stage turbine disk rotors
Turbine turbine internal cooling channel, first order turbine wheel disc 5 and its component and second level turbine wheel disc 12 and its component revolving speed
Difference, and first order turbine wheel disk rotating speed 5 is greater than 12 revolving speed of second level turbine wheel disc, using chamber, hole, the structural details such as obturages
Flow path control and assignment of traffic are carried out to turbine rotor inside, can satisfy cooling system for not coaxial different rotating speeds two-stage
Inside turbine offer movable vane piece cooling air, cooling turbine wheel disc, heat-insulated function, used cooling are obturaged to main blast tube
Medium is the compressed air from compressor extraction not at the same level.
Specific embodiment 2: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
The inside cooling structure of rotor, the upper end of the cooling air guiding device 1 is using labyrinth gas seals structure 3 and first order turbine
The top of wheel disc 5 is coupled, and the middle part of cooling air guiding device 1 and the middle part of first order turbine wheel disc 5 are using the first comb
Tooth sealing structure 35 is coupled, and blade bottom is formed on the top of cooling air guiding device 1 and the top of first order turbine wheel disc 5
Portion's chamber 36；The lower part of the cooling air guiding device 1 connects shell, and shell is equipped with gas tight jacket 33, and gas tight jacket 33 is adopted
It is coupled with the second comb tooth sealing structure 32 and turbine front end axis 29, cooling air guiding device 1, shell 41, the first order are saturating
Flat wheel disc 5 and gas tight jacket 33 form first order turbine wheel disc front chamber 34；Add in the axial direction of the cooling air guiding device 1
Work has multiple third through-holes 2, and 5 top of first order turbine wheel disc is machined with hole 4 on multiple first order wheel discs, third through-hole
2 and first order wheel disc on hole 4 be connected to respectively with blade bottom chamber 36, compressor exhaust cooling air-flow led by cooling air
First order turbine rotor vane leaf is passed through by hole 4 on first order wheel disc after entering blade bottom chamber 36 to the third through-hole 2 of device 1
Piece root；The middle position of the first order turbine wheel disc 5 is machined with multiple fourth holes 37, the first order turbine wheel
Disk front chamber 34 is connected to by fourth hole 37 with first order turbine wheel disc rear chamber 9.So set, one of compressor exhaust
Lease making crosses the third through-hole 2 before first order turbine wheel disc above cooling air guiding device 1 and flows into 5 movable vane of first order turbine wheel disc
Blade bottom chamber 36, a part become owner of blast tube, another portion by heel row on front side of the cooling root of blade of labyrinth gas seals structure 3
Divide and first order turbine rotor vane bottom is passed through by hole 4 on first order wheel disc；Compressor hiigh pressure stage bleed is by gas tight jacket 33 and thoroughly
The second comb tooth sealing structure 32 that flat front end axis 29 is formed flows into first order turbine wheel disc front chamber 34, cooling first order turbine
It is divided into 2 strands of air-flows after on front side of wheel disc, wherein one passes through the between cooling air guiding device 1 and first order turbine wheel disc 5
Blade bottom chamber 36 is met at compressor exhaust airstream after one comb tooth sealing structure 35；Another stock then passes through first order turbine
Several fourth holes 37 of axis on wheel disc 5 are passed through the subsequent first order turbine wheel disc rear chamber 9 of first order turbine wheel disc 5, cooling
With 8 front side of spacer member on rear side of first order turbine wheel disc, two parts are further divided into, a part of air-flow is saturating by spacer member 8 and the first order
Third comb tooth sealing structure 19 between flat wheel disc disk 5 is passed through second level turbine wheel disc front chamber 13, and another part passes through first
Grade turbine wheel disc 5 is formed by rear side of the cooling first order turbine blade roots of the 4th comb tooth sealing structure 6 with 7 front of stator blade inner ring
Main blast tube is flowed into behind stator blade inner ring front side.
Specific embodiment 3: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
The inside cooling structure of rotor, the lower end for the spacer member 8 installed in the stator blade inner ring 7 is using third comb tooth sealing structure 19
It is coupled with the lower end of first order turbine wheel disc 5.
Specific embodiment 4: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
The 4th comb tooth sealing structure the 6, the 5th comb is respectively adopted in the inside cooling structure of rotor, the left and right ends of the stator blade inner ring 7
Tooth sealing structure 10 is coupled with first order turbine wheel disc 5, second level turbine wheel disc 12.
Specific embodiment 5: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
Pacify inside the between centers circulation chamber 40 that the inside cooling structure of rotor, the turbine rear axle 20 and turbine front end axis 29 are formed
Equipped with air introduction 27, between centers circulation chamber 40 is separated to form compressor sub-high pressure grade tap air channel 28 by air introduction 27
With compressor low-pressure stage tap air channel 26, axle sleeve 22, axle sleeve 22 and turbine front end axis are installed in the turbine rear axle 20
By the 6th comb tooth sealing structure 23 between 29, axial ring gap 21 is formed between axle sleeve 22 and second level turbine wheel disc 12,
Compressor low-pressure stage tap air channel 26 is connected to by the 6th comb tooth sealing structure 23 with lower chamber 24 between two-stage disk stage, together
When, compressor low-pressure stage tap air channel 26 is connected to by axial ring gap 21 with second level turbine wheel disc lower part cooling chamber 18；
Level-one turbine wheel pan bottom cooling chamber 31 is formed between the turbine front end axis 29 and first order turbine wheel disc 5, it is described
Multiple second through-holes 30 are radially machined on turbine front end axis 29, the compressor sub-high pressure grade tap air channel 28 passes through second
Through-hole 30 is connected to level-one turbine wheel pan bottom cooling chamber 31, level-one turbine wheel pan bottom cooling chamber 31 and two-stage disk stage
Between lower chamber 24 be connected to.So set, compressor low-pressure stage bleed, is formed by turbine rear axle 20 and air introduction 27
Compressor low-pressure stage tap air channel 26, after the 6th comb tooth sealing structure 23 flow into two-stage disk stage between lower chamber 24；
Compressor sub-high pressure grade bleed, by inside center compressor sub-high pressure grade tap air channel 28, using on turbine front end axis 29
Several second through-holes 30 be passed through the level-one turbine wheel pan bottom cooling chamber 31 of first order turbine wheel disc 5, the cooling first order is saturating
Behind flat wheel disc lower part, lower chamber 24 between two-stage disk stage is reached；After lower chamber 24 is converged between the above two-stage disk stage, then divide
For two strands of air-flows:
Wherein one air-flow along radial inflow to second level turbine wheel disc front chamber 13, and with the portion from hiigh pressure stage
Cooling air is divided to converge, the front side of cooling second level turbine wheel disc 12 and the rear side of spacer member 8, then a part passes through the second level
Hole 11 is passed through second level turbine rotor vane bottom on second level wheel disc on turbine wheel disc disk, and another part passes through in the stator blade of the second level
7 rear portion of ring and 12 front of second level turbine wheel disc are formed by rear side of the cooling stator blade inner ring of the 5th comb tooth sealing structure 10 and second
Main blast tube is flowed into after on front side of grade turbine wheel disc root of blade；
Another stock is saturating along the cooling second level of axial ring gap 21 between second level turbine wheel pan bottom and axle sleeve 22
The second level turbine wheel disc lower part cooling chamber 18 of second level turbine wheel disc and the formation of turbine rear axle 20 is flowed into behind flat wheel pan bottom,
Second level turbine wheel disc rear chamber 16 is flowed to outward further along several first through hole 17 in the turbine wheel back-end disk structure of the second level,
Main blast tube is discharged to by the 7th comb tooth sealing structure 14 after on rear side of the cooling second level turbine wheel disc of journey, while cooling the
On rear side of second level turbine wheel disc root of blade.
Specific embodiment 6: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
The inside cooling structure of rotor, the top of the second level turbine wheel disc 12 are machined with hole 11 on multiple second level wheel discs, the
Hole 11 is connected to second level turbine wheel disc front chamber 13 on second level wheel disc, into the cooling air of second level turbine wheel disc front chamber 13
Stream leads to second level turbine rotor vane blade by hole 11 on the wheel disc of the second level.
Specific embodiment 7: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
The inside cooling structure of rotor passes through the 7th comb tooth sealing structure between the second level turbine wheel disc 12 and turbine cylinder body 15
14 are coupled, and the cooling air-flow into second level turbine wheel disc rear chamber 16 flows through cooling the after the 7th comb tooth sealing structure 14
On rear side of second level turbine rotor vane root of blade.
Specific embodiment 8: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment
The inside cooling structure of rotor, the first order turbine wheel disc 5 are connected by screw bolts mode and are fixedly mounted on level-one turbine wheel
In disk connection ring 38, the second level turbine wheel disc 12 is fixedly mounted in second level turbine wheel disc connection ring 39.
This embodiment is just an exemplary description of this patent, does not limit its protection scope, those skilled in the art
Member can also be changed its part, as long as it does not exceed the essence of this patent, within the protection scope of the present patent.
Claims (10)
1. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine, including cooling air guiding device (1), the first order are saturating
Flat wheel disc (5), second level turbine wheel disc (12), turbine front end axis (29), turbine rear axle (20) and shell (41), described is saturating
Flat front end axis (29) is hollow shaft, and turbine rear axle (20) setting is in the turbine front end axis (29), turbine front end axis (29) and thoroughly
The concentric arrangement of flat rear axle (20), the circumferential direction of the turbine front end axis (29) are provided with level-one turbine wheel disc connection ring
(38), the circumferential direction of the turbine rear axle (20) is provided with second level turbine wheel disc connection ring (39), first order turbine wheel disc (5)
It is fixedly mounted in level-one turbine wheel disc connection ring (38), second level turbine wheel disc (12) is fixedly mounted on second level turbine wheel disc company
It connects on ring (39), it is characterised in that:
The cooling air guiding device (1) is used to introduce the cooling air-flow of the gas turbine from compressor exhaust, cooling
Air-deflector (1) and first order turbine wheel disc (5) form blade bottom chamber (36), shell (41) and first order turbine wheel
Disk (5) forms first order turbine wheel disc front chamber (34), and cooling air-flow flows through first order turbine wheel disc front chamber (34) and blade
Bottom chamber (36) cools down first order root of blade afterwards；
Stator blade inner ring (7) are equipped between the first order turbine wheel disc (5) and second level turbine wheel disc (12), stator blade inner ring
(7) it is equipped on spacer member (8), spacer member (8) will separate between first order turbine wheel disc (5) and second level turbine wheel disc (12)
It forms first order turbine wheel disc rear chamber (9) and second level turbine wheel disc front chamber (13), cooling air-flow flows through first order turbine
Wheel disc rear chamber (9) and second level turbine wheel disc front chamber (13) are cooled down on rear side of first order root of blade afterwards and second level blade root
Portion；
Lower chamber between two-stage disk stage is formed at first order turbine wheel disc (5) lower part and second level turbine wheel disc (12) lower part
Room (24), turbine front end axis (29) is internal to form between centers circulation chamber (40) with turbine rear axle, between centers circulation chamber (40) with
Lower chamber (24) is connected between two-stage disk stage；
The second level turbine wheel disc connection ring (39) that the second level turbine wheel disc (12) and turbine rear axle (20) is circumferentially arranged
It is formed second level turbine wheel disc lower part cooling chamber (18), the second level turbine wheel disc (12) and second level turbine wheel disc connection ring
(39) installation place is radially machined with multiple first through hole (17), the second level turbine wheel disc (12) and turbine cylinder body (15)
Between form second level turbine wheel disc rear chamber (16), the cooling air-flow for flowing through lower chamber (24) between two-stage disk stage flows into two
Grade turbine wheel disc lower part cooling chamber (18), and it is cold afterwards into second level turbine wheel disc rear chamber (16) by first through hole (17)
But on rear side of the root of blade of the second level.
2. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
The upper end for the cooling air guiding device (1) stated is cooperated using labyrinth gas seals structure (3) and the top of first order turbine wheel disc (5)
Installation, the middle part of cooling air guiding device (1) and the middle part of first order turbine wheel disc (5) use the first comb tooth sealing structure
(35) it is coupled, blade bottom chamber is formed on the top of cooling air guiding device (1) and the top of first order turbine wheel disc (5)
Room (36)；The lower part of the cooling air guiding device (1) is connected with shell (41), and shell is equipped with gas tight jacket on (41)
(33), gas tight jacket (33) is coupled using the second comb tooth sealing structure (32) with turbine front end axis (29), cooling air guiding
Device (1), shell (41), first order turbine wheel disc (5) and gas tight jacket (33) form first order turbine wheel disc front chamber (34).
3. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
The lower end for the spacer member (8) installed in the stator blade inner ring (7) stated is using third comb tooth sealing structure (19) and first order turbine wheel
The lower end of disk (5) is coupled.
4. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
The 4th comb tooth sealing structure (6), the 5th comb tooth sealing structure (10) and the is respectively adopted in the left and right ends for the stator blade inner ring (7) stated
Level-one turbine wheel disc (5), second level turbine wheel disc (12) are coupled.
5. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
Air introduction is installed inside the between centers circulation chamber (40) that the turbine rear axle (20) and turbine front end axis (29) stated are formed
(27), between centers circulation chamber (40) is separated to form compressor sub-high pressure grade tap air channel (28) and calmed the anger by air introduction (27)
Machine low-pressure stage tap air channel (26) is equipped with axle sleeve (22) in the turbine rear axle (20), axle sleeve (22) and turbine front end
By the 6th comb tooth sealing structure (23) between axis (29), axial rings are formed between axle sleeve (22) and second level turbine wheel disc (12)
Shape gap (21), compressor low-pressure stage tap air channel (26) pass through lower part between the 6th comb tooth sealing structure (23) and two-stage disk stage
Chamber (24) connection, meanwhile, compressor low-pressure stage tap air channel (26) passes through axial ring gap (21) and second level turbine wheel disc
Lower part cooling chamber (18) connection.
6. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 5, it is characterised in that: institute
Level-one turbine wheel pan bottom cooling chamber (31) are formed between the turbine front end axis (29) stated and first order turbine wheel disc (5), institute
Multiple second through-holes (30), the compressor sub-high pressure grade tap air channel are radially machined on the turbine front end axis (29) stated
(28) it is connected to by the second through-hole (30) with level-one turbine wheel pan bottom cooling chamber (31), level-one turbine wheel pan bottom cooling chamber
Room (31) is connected to lower chamber (24) between two-stage disk stage.
7. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
It is machined in the axial direction for the cooling air guiding device (1) stated multiple third through-holes (2), the first order turbine wheel disc (5)
Top is machined with hole (4) on multiple first order wheel discs, on third through-hole (2) and the first order wheel disc hole (4) respectively with blade bottom
The cooling air-flow of chamber (36) connection, compressor exhaust enters blade by the third through-hole (2) of cooling air guiding device (1)
Bottom chamber (36) is passed through first order turbine rotor vane root of blade by hole (4) on first order wheel disc afterwards；
The middle position of the first order turbine wheel disc (5) is machined with multiple fourth holes (37), the first order turbine
Wheel disc front chamber (34) is connected to by fourth hole (37) with first order turbine wheel disc rear chamber (9).
8. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
The top for the second level turbine wheel disc (12) stated is machined with hole (11) on multiple second level wheel discs, on the wheel disc of the second level hole (11) with
Second level turbine wheel disc front chamber (13) connection, the cooling air-flow into second level turbine wheel disc front chamber (13) pass through the second level
Hole (11) are passed through second level turbine rotor vane root of blade on wheel disc.
9. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
It is coupled, is entered by the 7th comb tooth sealing structure (14) between the second level turbine wheel disc (12) stated and turbine cylinder body (15)
The cooling air-flow of second level turbine wheel disc rear chamber (16) flows through the 7th comb tooth sealing structure (14), and cooling second level turbine is dynamic afterwards
On rear side of leaf root of blade.
10. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute
First order turbine wheel disc (5) mode of being connected by screw bolts stated is fixedly mounted in level-one turbine wheel disc connection ring (38), described
Second level turbine wheel disc (12) be fixedly mounted in second level turbine wheel disc connection ring (39).
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| CN201811320228.3A CN109139122B (en) | 2018-11-07 | 2018-11-07 | Internal cooling system of 2-stage turbine rotor of gas turbine |
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| CN201811320228.3A CN109139122B (en) | 2018-11-07 | 2018-11-07 | Internal cooling system of 2-stage turbine rotor of gas turbine |
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| CN109139122B CN109139122B (en) | 2023-09-19 |
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Cited By (9)
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| CN109798153A (en) * | 2019-03-28 | 2019-05-24 | 中国船舶重工集团公司第七0三研究所 | A kind of cooling structure applied to marine gas turbine wheel disk of turbine |
| CN110656984A (en) * | 2019-07-29 | 2020-01-07 | 中国航发沈阳发动机研究所 | Device and method for measuring airflow at outlet of disk edge position of turbine disk |
| CN111894734A (en) * | 2020-08-12 | 2020-11-06 | 哈电发电设备国家工程研究中心有限公司 | Turbine of small and medium-sized gas turbine and working method |
| CN112432793A (en) * | 2020-11-23 | 2021-03-02 | 东方电气集团东方汽轮机有限公司 | Gas turbine wheel disc air extraction test piece and modeling test parameter design method |
| CN112444398A (en) * | 2020-11-23 | 2021-03-05 | 东方电气集团东方汽轮机有限公司 | Gas turbine rotor cold air conveying test piece and test parameter design method |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
| CN114215611A (en) * | 2021-12-01 | 2022-03-22 | 东方电气集团东方汽轮机有限公司 | Gas encapsulation ligand for axial positioning of turbine moving blade of gas turbine |
| CN114776402A (en) * | 2021-01-22 | 2022-07-22 | 中国航发商用航空发动机有限责任公司 | Bearing cavity sealing system of aircraft engine and control method thereof |
| CN115788677A (en) * | 2022-11-18 | 2023-03-14 | 中国联合重型燃气轮机技术有限公司 | Gas turbine torque disc air supply flow path structure and gas turbine |
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| CN109798153A (en) * | 2019-03-28 | 2019-05-24 | 中国船舶重工集团公司第七0三研究所 | A kind of cooling structure applied to marine gas turbine wheel disk of turbine |
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| CN112444398A (en) * | 2020-11-23 | 2021-03-05 | 东方电气集团东方汽轮机有限公司 | Gas turbine rotor cold air conveying test piece and test parameter design method |
| CN114776402A (en) * | 2021-01-22 | 2022-07-22 | 中国航发商用航空发动机有限责任公司 | Bearing cavity sealing system of aircraft engine and control method thereof |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
| CN114215611A (en) * | 2021-12-01 | 2022-03-22 | 东方电气集团东方汽轮机有限公司 | Gas encapsulation ligand for axial positioning of turbine moving blade of gas turbine |
| CN114215611B (en) * | 2021-12-01 | 2023-07-14 | 东方电气集团东方汽轮机有限公司 | Gas seal assembly for axial positioning of turbine movable blade of gas turbine |
| CN115788677A (en) * | 2022-11-18 | 2023-03-14 | 中国联合重型燃气轮机技术有限公司 | Gas turbine torque disc air supply flow path structure and gas turbine |
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| CN109139122B (en) | 2023-09-19 |
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