CN109798153A - A kind of cooling structure applied to marine gas turbine wheel disk of turbine - Google Patents
A kind of cooling structure applied to marine gas turbine wheel disk of turbine Download PDFInfo
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- CN109798153A CN109798153A CN201910244034.8A CN201910244034A CN109798153A CN 109798153 A CN109798153 A CN 109798153A CN 201910244034 A CN201910244034 A CN 201910244034A CN 109798153 A CN109798153 A CN 109798153A
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Abstract
A kind of cooling structure applied to marine gas turbine wheel disk of turbine is related to a kind of cooling structure of Gas Turbine wheel disc.The present invention is to solve the bad technical problems of the cooling effect of existing marine gas turbine wheel disk of turbine.Cooling structure applied to marine gas turbine wheel disk of turbine of the invention is made of annular partition, annular lid and bend pipe；The end face outside of annular lid is matched with the inner side end of annular partition, multiple bolts fix annular lid with annular partition, fourth annular protrusion forms cooling air channel in the outside of first annular protrusion, the region that fourth annular protrusion, oblique groove and first annular protrusion are surrounded.The present invention provides a kind of cooling structure applied to marine gas turbine wheel disk of turbine, this structure has carried out efficient cooling to wheel disk of turbine, effectively improves the stress condition of wheel disk of turbine, increases the service life of wheel disc, improves unit reliability of operation.
Description
Technical field
The present invention relates to a kind of cooling structures of Gas Turbine wheel disc.
Background technique
In the gas turbine, wheel disk of turbine is stress one of component the most complicated, is subjected to combustion gas flow area biography
The high-temperature load come is passed, while bearing itself and blade bring centrifugal load.Marine gas turbine is due to its special work
Situations such as rapid starting/stopping, variable working condition and combustor exit temperature are uneven can be had by making property, lead to the work of wheel disk of turbine
Condition complex.With the continuous improvement of combustor exit temperature, this will lead to, and wheel disc thermic load is improved, thermal stress increases,
Margin of safety decline.Therefore it needs to carry out efficient cooling structure design to turbine, improves the service life of wheel disc.
Summary of the invention
The present invention is to solve the bad technical problems of the cooling effect of existing marine gas turbine wheel disk of turbine, and mention
For a kind of cooling structure applied to marine gas turbine wheel disk of turbine.
Cooling structure applied to marine gas turbine wheel disk of turbine of the invention is by annular partition 1,2 and of annular lid
Bend pipe 4 forms；
The annular partition 1 is ring structure, multiple air inlet 1-1 is uniformly arranged in the side of annular partition 1, in ring
Multiple first bolt hole 1-3 are uniformly arranged at the inner side end outer of shape partition 1, annular partition 1 inner side end from first
Bolt hole 1-3 sets gradually first annular protrusion 1-6 and the second annular protrusion 1-7 to center of circle direction, in first annular protrusion 1-6
End be circumferentially uniformly arranged multiple oblique protrusions, be an oblique groove 1- between the oblique protrusion of connected two
5；The outlet normal direction and wheel side surface of the oblique groove 1-5 is at 15 °, and the air-flow flowed out from oblique groove 1-5,
The tangential direction of flowing is contrary with wheel disc rolling tangential；Between the first bolt hole 1-3 and first annular protrusion 1-6 uniformly
Multiple gas outlet 1-4 are set, and the outgassing direction of gas outlet 1-4 is against first annular protrusion 1-6, gas outlet 1-4 and air inlet 1-1
Quantity is equal and a gas outlet 1-4 and an air inlet 1-1 correspond connection；
The annular lid 2 is ring structure, and multiple the are uniformly arranged at the outer of the inner side end of annular lid 2
Two bolt hole 2-1, the quantity of the second bolt hole 2-1 is identical as the first bolt hole 1-3, annular lid 2 inner side end from
Two bolt hole 2-1 set gradually third annular protrusion 2-2 and fourth annular protrusion 2-3 to center of circle direction, in the outer of annular lid 2
One annular groove 2-4 is set at the outer of side end face；
The end face outside of the annular lid 2 and the inner side end of annular partition 1 cooperate, and multiple bolts 3 are successively
Across the second bolt hole 2-1 and the first bolt hole 1-3 that annular lid 2 is fixed with annular partition 1, fourth annular protrusion 2-3 exists
The region that the outside of first annular protrusion 1-6, fourth annular protrusion 2-3, oblique groove 1-5 and first annular protrusion 1-6 surround
Form cooling air channel 1-2；In one air inlet 1-1 of one end insertion annular partition 1 of each bend pipe 4, bend pipe 4 with
One air inlet 1-1 is corresponded, at the cooling air outlet of the other end insertion guide vane 5 of bend pipe 4.
The application method of cooling structure applied to marine gas turbine wheel disk of turbine of the invention is as follows: guide vane 5 passes through
Bolt is fixed on the inner surface of casing 7, and annular partition 1 and annular lid 2 are fixed on the inframarginal of guide vane 5, the upper end of bend pipe 4 with
The lower end gas outlet of guide vane 5 is connected to, and forms cooling air runner in inside, outlet passageway 1-2 corresponds to 8 air inlet side spoke end of wheel disc
Face, the outlet normal direction and wheel side surface of oblique groove 1-5 is at 15 °, and the air-flow of the outflow from oblique groove 1-5, stream
Dynamic tangential direction is contrary with wheel disc rolling tangential；The annular protrusion of the annular protrusion 2-2 of annular lid 2, annular partition 1
1-6 and annular protrusion 1-7 successively forms sealing structure with three comb teeth of wheel disc 8；The annular groove 2-4 of annular lid 2 is used for
Sealing ring 9 is placed, sealing ring 9 is matched with the lower part of guide vane 5 and is sealed.
Annular cooling air runner and the inner cavity of guide vane 5 are connected by bend pipe 4, the both ends of bend pipe 4 and guide vane 5 and it is annular every
Plate 1 forms tight fit face, reduces the leakage of air.
The cooling air of the cooling system is provided by compressor, and cooling air passes through the air intake on 7 surface of turbine casing
It flows into turbine guide vane 5, is hollow core structures inside turbine guide vane 5, and then annular partition 1 and annular lid 2 are flowed by bend pipe 4
The annular air runner of composition, is finally flowed out by outlet passageway 1-2.
The present invention provides a kind of cooling structure applied to marine gas turbine wheel disk of turbine, this structure to wheel disk of turbine into
It has gone efficient cooling, has enhanced sheave surface heat transfer effect, effectively improve the stress condition of wheel disk of turbine, increase wheel
The service life of disk improves unit reliability of operation.
Detailed description of the invention
Fig. 1 is the plane after the cooling structure installation applied to marine gas turbine wheel disk of turbine of specific embodiment one
Schematic diagram；
Fig. 2 is the part after the cooling structure installation applied to marine gas turbine wheel disk of turbine of specific embodiment one
Stereoscopic schematic diagram；
Fig. 3 is annular partition 1 in the cooling structure applied to marine gas turbine wheel disk of turbine of specific embodiment one
With the stereoscopic schematic diagram after the combination of annular lid 2；
Fig. 4 is the top half of the sectional view of A-A in Fig. 3；
Fig. 5 is the partial enlarged view of Fig. 3；
Fig. 6 is the front view of the annular partition 1 of specific embodiment one；
Fig. 7 is the stereoscopic schematic diagram of the annular partition 1 of specific embodiment one；
Fig. 8 is the partial enlarged view of Fig. 7；
Fig. 9 is the top half of the sectional view of B-B in Fig. 7；
Figure 10 is the enlarged drawing of the oblique groove 1-5 of Fig. 7；
Figure 11 is the partial top view of Figure 10；
Figure 12 is the stereoscopic schematic diagram of the annular partition 1 of specific embodiment one；
Figure 13 is the front view of the annular lid 2 of specific embodiment one；
Figure 14 is the stereoscopic schematic diagram of the annular lid 2 of specific embodiment one；
Figure 15 is the partial enlarged view of Figure 14；
Figure 16 is the top half of the sectional view of C-C in Figure 14.
Specific embodiment
Specific embodiment 1: present embodiment is a kind of cooling structure applied to marine gas turbine wheel disk of turbine,
As shown in figure Fig. 3-Figure 16, specifically it is made of annular partition 1, annular lid 2 and bend pipe 4；
The annular partition 1 is ring structure, multiple air inlet 1-1 is uniformly arranged in the side of annular partition 1, in ring
Multiple first bolt hole 1-3 are uniformly arranged at the inner side end outer of shape partition 1, annular partition 1 inner side end from first
Bolt hole 1-3 sets gradually first annular protrusion 1-6 and the second annular protrusion 1-7 to center of circle direction, in first annular protrusion 1-6
End be circumferentially uniformly arranged multiple oblique protrusions, be an oblique groove 1- between the oblique protrusion of connected two
5；The outlet normal direction and wheel side surface of the oblique groove 1-5 is at 15 °, and the air-flow flowed out from oblique groove 1-5,
The tangential direction of flowing is contrary with wheel disc rolling tangential；Between the first bolt hole 1-3 and first annular protrusion 1-6 uniformly
Multiple gas outlet 1-4 are set, and the outgassing direction of gas outlet 1-4 is against first annular protrusion 1-6, gas outlet 1-4 and air inlet 1-1
Quantity is equal and a gas outlet 1-4 and an air inlet 1-1 correspond connection；
The annular lid 2 is ring structure, and multiple the are uniformly arranged at the outer of the inner side end of annular lid 2
Two bolt hole 2-1, the quantity of the second bolt hole 2-1 is identical as the first bolt hole 1-3, annular lid 2 inner side end from
Two bolt hole 2-1 set gradually third annular protrusion 2-2 and fourth annular protrusion 2-3 to center of circle direction, in the outer of annular lid 2
One annular groove 2-4 is set at the outer of side end face；
The end face outside of the annular lid 2 and the inner side end of annular partition 1 cooperate, and multiple bolts 3 are successively
Across the second bolt hole 2-1 and the first bolt hole 1-3 that annular lid 2 is fixed with annular partition 1, fourth annular protrusion 2-3 exists
The region that the outside of first annular protrusion 1-6, fourth annular protrusion 2-3, oblique groove 1-5 and first annular protrusion 1-6 surround
Form cooling air channel 1-2；In one air inlet 1-1 of one end insertion annular partition 1 of each bend pipe 4, bend pipe 4 with
One air inlet 1-1 is corresponded, at the cooling air outlet of the other end insertion guide vane 5 of bend pipe 4.
The application method of the cooling structure applied to marine gas turbine wheel disk of turbine of present embodiment is as follows: such as Fig. 1-
Shown in Fig. 2, arrow is the flow direction of cooling air, and guide vane 5 is bolted on the inner surface of casing 7, annular partition 1 with
Annular lid 2 is fixed on the inframarginal of guide vane 5, and the upper end opening of bend pipe 4 is connected to the lower end of guide vane 5, forms cooling in inside
Air flow channel, outlet passageway 1-2 correspond to 8 air inlet side spoke end face of wheel disc, the outlet normal direction of oblique groove 1-5 and wheel disc end
Face is at 15 °, and the air-flow flowed out from oblique groove 1-5, and the tangential direction of flowing is contrary with wheel disc rolling tangential；
The annular protrusion 2-2 of annular lid 2, the annular protrusion 1-6 of annular partition 1 and annular protrusion 1-7 successively with wheel disc 8
Three comb teeth formed sealing structure；The annular groove 2-4 of annular lid 2 is for placing sealing ring 9, sealing ring 9 and guide vane 5
Lower part is cooperated, seal gas.
Annular cooling air runner and the inner cavity of guide vane 5 are connected by bend pipe 4, the both ends of bend pipe 4 and guide vane 5 and it is annular every
Plate 1 forms tight fit face, reduces the leakage of air.
The cooling air of the cooling system is provided by compressor, and cooling air passes through the air intake on 7 surface of turbine casing
It flows into turbine guide vane 5, is hollow core structures inside turbine guide vane 5, and then annular partition 1 and annular lid 2 are flowed by bend pipe 4
The annular air runner of composition, is finally flowed out by outlet passageway 1-2.
Present embodiment provides a kind of cooling structure applied to marine gas turbine wheel disk of turbine, this structure is to turbine wheel
Disk has carried out efficient cooling, enhances sheave surface heat transfer effect, reduces disk temperature, effectively improves wheel disk of turbine
Stress condition increases the service life of wheel disc, improves unit reliability of operation.
The outlet normal direction of the oblique groove 1-5 of present embodiment and 8 end face of wheel disc increase 8 surface of wheel disc at 15 °
Flowing velocity between air enhances heat transfer effect.
Specific embodiment 2: the present embodiment is different from the first embodiment in that: the oblique groove 1-5's
Section is the rectangle of width 3.4mm, high 4mm.Other are same as the specific embodiment one.
Specific embodiment 3: the present embodiment is different from the first and the second embodiment in that: the outlet passageway
1-2 is 108.Other are the same as one or two specific embodiments.
Specific embodiment 4: present embodiment is unlike specific embodiment three: the bolt 3 is 42.
Other are the same as the specific implementation mode 3.
Specific embodiment 5: present embodiment is unlike specific embodiment four: the air inlet 1-1 is 42
It is a.Other are identical as specific embodiment four.
The present invention is verified with following tests:
Test one: this test is a kind of cooling structure applied to marine gas turbine wheel disk of turbine, such as Fig. 3-Figure 16 institute
Show, is specifically made of annular partition 1, annular lid 2 and bend pipe 4；
The annular partition 1 is ring structure, multiple air inlet 1-1 is uniformly arranged in the side of annular partition 1, in ring
Multiple first bolt hole 1-3 are uniformly arranged at the inner side end outer of shape partition 1, annular partition 1 inner side end from first
Bolt hole 1-3 sets gradually first annular protrusion 1-6 and the second annular protrusion 1-7 to center of circle direction, in first annular protrusion 1-6
End be circumferentially uniformly arranged multiple oblique protrusions, be an oblique groove 1- between the oblique protrusion of connected two
5；The outlet normal direction and wheel side surface of the oblique groove 1-5 is at 15 °, and the air-flow flowed out from oblique groove 1-5,
The tangential direction of flowing is contrary with wheel disc rolling tangential；Between the first bolt hole 1-3 and first annular protrusion 1-6 uniformly
Multiple gas outlet 1-4 are set, and the outgassing direction of gas outlet 1-4 is against first annular protrusion 1-6, gas outlet 1-4 and air inlet 1-1
Quantity it is equal, and a gas outlet 1-4 and air inlet 1-1 corresponds connection；
The annular lid 2 is ring structure, and multiple the are uniformly arranged at the outer of the inner side end of annular lid 2
Two bolt hole 2-1, the quantity of the second bolt hole 2-1 is identical as the first bolt hole 1-3, annular lid 2 inner side end from
Two bolt hole 2-1 set gradually third annular protrusion 2-2 and fourth annular protrusion 2-3 to center of circle direction, in the outer of annular lid 2
One annular groove 2-4 is set at the outer of side end face；
The end face outside of the annular lid 2 and the inner side end of annular partition 1 cooperate, and multiple bolts 3 are successively
Across the second bolt hole 2-1 and the first bolt hole 1-3, annular lid 2 is fixed with annular partition 1, and fourth annular protrusion 2-3 exists
The region that the outside of first annular protrusion 1-6, fourth annular protrusion 2-3, oblique groove 1-5 and first annular protrusion 1-6 surround
Form cooling air channel 1-2；In one air inlet 1-1 of one end insertion annular partition 1 of each bend pipe 4, bend pipe 4 with
One air inlet 1-1 is corresponded, at the cooling air outlet of the other end insertion guide vane 5 of bend pipe 4.
The application method of the cooling structure applied to marine gas turbine wheel disk of turbine of this test is as follows: as shown in Figure 1,
Arrow is the flow direction of cooling air, and guide vane 5 is bolted on the inner surface of casing 7, annular partition 1 and annular lid
2 are fixed on the inframarginal of guide vane 5, and the upper end opening of bend pipe 4 is connected to the lower end gas outlet of guide vane 5, are formed in inside cooling empty
Flow channel, outlet passageway 1-2 correspond to 8 air inlet side spoke end face of wheel disc, the outlet normal direction and wheel side surface of oblique groove 1-5
At 15 °, and the air-flow flowed out from oblique groove 1-5, the tangential direction of flowing are contrary with wheel disc rolling tangential；Ring cover
The third annular protrusion 2-2 of body 2, annular partition 1 annular protrusion 1-6 and annular protrusion 1-7 successively with three comb teeth of wheel disc 8
Form sealing structure；The annular groove 2-4 of annular lid 2 is for placing sealing ring 9, the lower part phase interworking of sealing ring 9 and guide vane 5
It closes, seal gas.
Annular cooling air runner and the inner cavity of guide vane 5 are connected by bend pipe 4, the both ends of bend pipe 4 and guide vane 5 and it is annular every
Plate 1 forms tight fit face, reduces the leakage of air.
The cooling air of the cooling system is provided by compressor, and cooling air passes through the air intake on 7 surface of turbine casing
It flows into turbine guide vane 5, is hollow core structures inside turbine guide vane 5, and then annular partition 1 and annular lid 2 are flowed by bend pipe 4
The annular air runner of composition, is finally flowed out by outlet passageway 1-2.
This test provides a kind of cooling structure applied to marine gas turbine wheel disk of turbine, this structure to wheel disk of turbine into
It has gone efficient cooling, has enhanced sheave surface heat transfer effect, reduced disk temperature, effectively improve the stress of wheel disk of turbine
Situation increases the service life of wheel disc, improves unit reliability of operation.
The outlet normal direction of the oblique groove 1-5 of this test and 8 end face of wheel disc at 15 °, increase 8 surface of wheel disc sky
The flowing velocity of gas enhances heat transfer effect.
The section of the oblique groove 1-5 is the rectangle of width 3.4mm, high 4mm；The outlet passageway 1-2 is 108
It is a；The bolt 3 is 42；The air inlet 1-1 is 42.
Claims (5)
1. a kind of cooling structure applied to marine gas turbine wheel disk of turbine, it is characterised in that be applied to marine gas turbine whirlpool
The cooling structure for taking turns wheel disc is made of annular partition (1), annular lid (2) and bend pipe (4)；
The annular partition (1) is ring structure, is uniformly arranged multiple air inlets (1-1) in the side of annular partition (1),
Multiple first bolts hole (1-3) are uniformly arranged at the inner side end outer of annular partition (1), in the inner end of annular partition (1)
Face sets gradually first annular raised (1-6) and the second annular protrusion (1-7) from the direction the first bolt hole (1-3) Xiang Yuanxin,
The end of first annular protrusion (1-6) is circumferentially uniformly arranged multiple oblique protrusions, two connected oblique protrusions
Between be an oblique groove (1-5)；The outlet normal direction of the oblique groove (1-5) and wheel side surface are at 15 °, and from oblique
The air-flow flowed out to groove (1-5), the tangential direction of flowing are contrary with wheel disc rolling tangential；In the first bolt hole (1-
3) it is uniformly arranged multiple gas outlets (1-4) between first annular raised (1-6), the outgassing direction of gas outlet (1-4) is against the
The quantity of one annular protrusion (1-6), gas outlet (1-4) and air inlet (1-1) is equal and a gas outlet (1-4) and an air inlet
Mouth (1-1) corresponds connection；
The annular lid (2) is ring structure, and multiple the are uniformly arranged at the outer of the inner side end of annular lid (2)
The quantity of two bolts hole (2-1), the second bolt hole (2-1) is identical as the first bolt hole (1-3), in the inside of annular lid (2)
End face sets gradually third annular protrusion (2-2) from the direction the second bolt hole (2-1) Xiang Yuanxin and fourth annular is raised (2-3),
One annular groove (2-4) is set at the outer of the end face outside of annular lid (2)；
The inner side end of the end face outside of the annular lid (2) and annular partition (1) cooperates, multiple bolts (3) according to
Secondary pass through the second bolt hole (2-1) and the first bolt hole (1-3) is fixed by annular lid (2) and annular partition (1), fourth annular
Raised (2-3) in the outside of first annular raised (1-6), fourth annular protrusion (2-3), oblique groove (1-5) with it is first annular
The region that raised (1-6) surrounds forms cooling air channel (1-2)；The one of one end insertion annular partition (1) of each bend pipe (4)
In a air inlet (1-1), a bend pipe (4) corresponds with an air inlet (1-1), and the other end of bend pipe (4) is inserted into guide vane
(5) at cooling air outlet.
2. a kind of cooling structure applied to marine gas turbine wheel disk of turbine according to claim 1, it is characterised in that
The section of the oblique groove (1-5) is the rectangle of width 3.4mm, high 4mm.
3. a kind of cooling structure applied to marine gas turbine wheel disk of turbine according to claim 1, it is characterised in that
The outlet passageway (1-2) is 108.
4. a kind of cooling structure applied to marine gas turbine wheel disk of turbine according to claim 3, it is characterised in that
The bolt (3) is 42.
5. a kind of cooling structure applied to marine gas turbine wheel disk of turbine according to claim 4, it is characterised in that
The air inlet (1-1) is 42.
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| CN201910244034.8A CN109798153B (en) | 2019-03-28 | 2019-03-28 | Cooling structure applied to turbine wheel disc of marine gas turbine |
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| CN201910244034.8A CN109798153B (en) | 2019-03-28 | 2019-03-28 | Cooling structure applied to turbine wheel disc of marine gas turbine |
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| CN109798153B CN109798153B (en) | 2023-08-22 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111794807A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | Power turbine inlet guider for fuel-drive compressor unit |
| CN112049688A (en) * | 2020-08-19 | 2020-12-08 | 西北工业大学 | Over-prerotation blade type receiving hole for equal-radius prerotation air supply system |
| CN114514360A (en) * | 2019-10-08 | 2022-05-17 | 赛峰飞机发动机公司 | Ejector for a high-pressure turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114514360A (en) * | 2019-10-08 | 2022-05-17 | 赛峰飞机发动机公司 | Ejector for a high-pressure turbine |
| CN111794807A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | Power turbine inlet guider for fuel-drive compressor unit |
| CN112049688A (en) * | 2020-08-19 | 2020-12-08 | 西北工业大学 | Over-prerotation blade type receiving hole for equal-radius prerotation air supply system |
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| CN109798153B (en) | 2023-08-22 |
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