CN109798153B - Cooling structure applied to turbine wheel disc of marine gas turbine - Google Patents
Cooling structure applied to turbine wheel disc of marine gas turbine Download PDFInfo
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- CN109798153B CN109798153B CN201910244034.8A CN201910244034A CN109798153B CN 109798153 B CN109798153 B CN 109798153B CN 201910244034 A CN201910244034 A CN 201910244034A CN 109798153 B CN109798153 B CN 109798153B
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Abstract
A cooling structure applied to a turbine wheel disc of a marine gas turbine relates to a cooling structure of the turbine wheel disc of the gas turbine. The invention aims to solve the technical problem that the cooling effect of the turbine wheel disc of the existing marine gas turbine is poor. The cooling structure applied to the turbine wheel disc of the marine gas turbine consists of an annular partition plate, an annular cover body and an elbow pipe; the outer side end face of the annular cover body is matched with the inner side end face of the annular partition plate, the annular cover body is fixed with the annular partition plate through a plurality of bolts, the fourth annular protrusion is arranged on the outer side of the first annular protrusion, and a cooling air channel is formed in the area surrounded by the fourth annular protrusion, the inclined groove and the first annular protrusion. The invention provides a cooling structure applied to a turbine wheel disc of a marine gas turbine, which is used for efficiently cooling the turbine wheel disc, effectively improving the stress condition of the turbine wheel disc, prolonging the service life of the wheel disc and improving the running reliability of a unit.
Description
Technical Field
The invention relates to a cooling structure of a turbine wheel disc of a gas turbine.
Background
In a gas turbine, a turbine disk is one of the most complex components to be subjected to centrifugal loads, as well as high-temperature loads transmitted from a gas flow region and centrifugal loads caused by blades. The special working property of the marine gas turbine can be rapid start-stop, variable working conditions, uneven temperature of the outlet of the combustion chamber and the like, so that the working condition of the turbine wheel disc is extremely complex. As the combustion chamber outlet temperature increases, this will result in an increase in disk thermal load, an increase in thermal stress, and a decrease in strength reserve. Therefore, the turbine needs to be efficiently cooled and the service life of the wheel disc is prolonged.
Disclosure of Invention
The invention aims to solve the technical problem that the cooling effect of the existing turbine wheel disc of the marine gas turbine is poor, and provides a cooling structure applied to the turbine wheel disc of the marine gas turbine.
The cooling structure applied to the turbine wheel disc of the marine gas turbine consists of an annular partition plate 1, an annular cover body 2 and an elbow 4;
the annular partition plate 1 is of an annular structure, a plurality of air inlets 1-1 are uniformly formed in the side face of the annular partition plate 1, a plurality of first bolt holes 1-3 are uniformly formed in the outer edge of the inner side end face of the annular partition plate 1, a first annular bulge 1-6 and a second annular bulge 1-7 are sequentially formed in the inner side end face of the annular partition plate 1 from the first bolt holes 1-3 to the circle center direction, a plurality of oblique bulges are uniformly formed in the tail end of the first annular bulge 1-6 along the circumferential direction, and an oblique groove 1-5 is formed between the two connected oblique bulges; the normal direction of the outlet section of the inclined groove 1-5 forms 15 degrees with the end face of the wheel disc, and the tangential direction of the air flow flowing out of the inclined groove 1-5 is opposite to the tangential direction of the rotation of the wheel disc; a plurality of air outlets 1-4 are uniformly arranged between the first bolt hole 1-3 and the first annular bulge 1-6, the air outlet direction of the air outlets 1-4 is opposite to the first annular bulge 1-6, the number of the air outlets 1-4 and the number of the air inlets 1-1 are equal, and one air outlet 1-4 is communicated with one air inlet 1-1 in a one-to-one correspondence manner;
the annular cover body 2 is of an annular structure, a plurality of second bolt holes 2-1 are uniformly formed in the outer edge of the inner side end face of the annular cover body 2, the number of the second bolt holes 2-1 is the same as that of the first bolt holes 1-3, a third annular bulge 2-2 and a fourth annular bulge 2-3 are sequentially formed in the inner side end face of the annular cover body 2 from the second bolt holes 2-1 to the circle center direction, and an annular groove 2-4 is formed in the outer edge of the outer side end face of the annular cover body 2;
the outer end face of the annular cover body 2 is matched with the inner end face of the annular partition plate 1, a plurality of bolts 3 sequentially penetrate through the second bolt holes 2-1 and the first bolt holes 1-3 to fix the annular cover body 2 and the annular partition plate 1, the fourth annular bulge 2-3 is arranged outside the first annular bulge 1-6, and a cooling air channel 1-2 is formed in the area surrounded by the fourth annular bulge 2-3, the inclined groove 1-5 and the first annular bulge 1-6; one end of each bent pipe 4 is inserted into one air inlet 1-1 of the annular partition plate 1, one bent pipe 4 corresponds to one air inlet 1-1 one by one, and the other end of the bent pipe 4 is inserted into a cooling air outlet of the guide vane 5.
The application method of the cooling structure applied to the turbine wheel disc of the marine gas turbine is as follows: the guide vane 5 is fixed on the inner surface of the casing 7 through bolts, the annular partition plate 1 and the annular cover body 2 are fixed on the lower edge plate of the guide vane 5, the upper end of the bent pipe 4 is communicated with the air outlet at the lower end of the guide vane 5, a cooling air flow channel is formed inside, the cooling air flow channel 1-2 corresponds to the air inlet side spoke end face of the wheel disc 8, the outlet section normal direction of the inclined groove 1-5 forms 15 degrees with the wheel disc end face, and the flowing out air flow from the inclined groove 1-5 has the tangential direction opposite to the rotation tangential direction of the wheel disc; the annular bulge 2-2 of the annular cover body 2, the annular bulge 1-6 of the annular partition plate 1 and the annular bulge 1-7 are sequentially provided with a sealing structure with three toothed racks of the wheel disc 8; the annular groove 2-4 of the annular cover body 2 is used for placing a sealing ring 9, and the sealing ring 9 is matched with the lower part of the guide vane 5 for sealing.
The annular cooling air flow passage is connected with the inner cavity of the guide vane 5 through the bent pipe 4, and two ends of the bent pipe 4 form a tight matching surface with the guide vane 5 and the annular partition plate 1, so that air leakage is reduced.
The cooling air of the cooling system is provided by a compressor, flows into the turbine guide vane 5 through an air inlet on the surface of the turbine casing 7, is of an air core structure inside the turbine guide vane 5, flows into an annular air flow channel formed by the annular partition plate 1 and the annular cover body 2 through the bent pipe 4, and finally flows out of the cooling air channel 1-2.
The invention provides a cooling structure applied to a turbine wheel disc of a marine gas turbine, which is used for efficiently cooling the turbine wheel disc, enhancing the heat exchange effect of the surface of the wheel disc, effectively improving the stress condition of the turbine wheel disc, prolonging the service life of the wheel disc and improving the running reliability of a unit.
Drawings
FIG. 1 is a schematic plan view of a cooling structure for a marine gas turbine disk according to one embodiment;
FIG. 2 is a partial perspective view of a cooling structure for a marine gas turbine disk according to one embodiment;
fig. 3 is a schematic perspective view showing a combination of an annular spacer 1 and an annular cover 2 in a cooling structure applied to a turbine disk of a marine gas turbine according to a first embodiment;
FIG. 4 is an upper half of the cross-sectional view of A-A of FIG. 3;
FIG. 5 is an enlarged view of a portion of FIG. 3;
fig. 6 is a front view of the annular separator 1 of the first embodiment;
fig. 7 is a schematic perspective view of the annular separator 1 according to the first embodiment;
FIG. 8 is an enlarged view of a portion of FIG. 7;
FIG. 9 is an upper half of the cross-sectional view of B-B of FIG. 7;
FIG. 10 is an enlarged view of the diagonal grooves 1-5 of FIG. 7;
FIG. 11 is a partial top view of FIG. 10;
fig. 12 is a schematic perspective view of the annular separator 1 according to the first embodiment;
fig. 13 is a front view of the annular cover 2 of the first embodiment;
fig. 14 is a schematic perspective view of the annular cover 2 according to the first embodiment;
FIG. 15 is an enlarged view of a portion of FIG. 14;
fig. 16 is an upper half of the cross-sectional view of fig. 14C-C.
Detailed Description
The first embodiment is as follows: the embodiment is a cooling structure applied to a turbine wheel disc of a marine gas turbine, as shown in fig. 3-16, and specifically comprises an annular partition plate 1, an annular cover body 2 and an elbow 4;
the annular partition plate 1 is of an annular structure, a plurality of air inlets 1-1 are uniformly formed in the side face of the annular partition plate 1, a plurality of first bolt holes 1-3 are uniformly formed in the outer edge of the inner side end face of the annular partition plate 1, a first annular bulge 1-6 and a second annular bulge 1-7 are sequentially formed in the inner side end face of the annular partition plate 1 from the first bolt holes 1-3 to the circle center direction, a plurality of oblique bulges are uniformly formed in the tail end of the first annular bulge 1-6 along the circumferential direction, and an oblique groove 1-5 is formed between the two connected oblique bulges; the normal direction of the outlet section of the inclined groove 1-5 forms 15 degrees with the end face of the wheel disc, and the tangential direction of the air flow flowing out of the inclined groove 1-5 is opposite to the tangential direction of the rotation of the wheel disc; a plurality of air outlets 1-4 are uniformly arranged between the first bolt hole 1-3 and the first annular bulge 1-6, the air outlet direction of the air outlets 1-4 is opposite to the first annular bulge 1-6, the number of the air outlets 1-4 and the number of the air inlets 1-1 are equal, and one air outlet 1-4 is communicated with one air inlet 1-1 in a one-to-one correspondence manner;
the annular cover body 2 is of an annular structure, a plurality of second bolt holes 2-1 are uniformly formed in the outer edge of the inner side end face of the annular cover body 2, the number of the second bolt holes 2-1 is the same as that of the first bolt holes 1-3, a third annular bulge 2-2 and a fourth annular bulge 2-3 are sequentially formed in the inner side end face of the annular cover body 2 from the second bolt holes 2-1 to the circle center direction, and an annular groove 2-4 is formed in the outer edge of the outer side end face of the annular cover body 2;
the outer end face of the annular cover body 2 is matched with the inner end face of the annular partition plate 1, a plurality of bolts 3 sequentially penetrate through the second bolt holes 2-1 and the first bolt holes 1-3 to fix the annular cover body 2 and the annular partition plate 1, the fourth annular bulge 2-3 is arranged outside the first annular bulge 1-6, and a cooling air channel 1-2 is formed in the area surrounded by the fourth annular bulge 2-3, the inclined groove 1-5 and the first annular bulge 1-6; one end of each bent pipe 4 is inserted into one air inlet 1-1 of the annular partition plate 1, one bent pipe 4 corresponds to one air inlet 1-1 one by one, and the other end of the bent pipe 4 is inserted into a cooling air outlet of the guide vane 5.
The method of using the cooling structure of the present embodiment applied to a marine gas turbine disk is as follows: as shown in fig. 1-2, arrows show the flowing direction of cooling air, the guide vane 5 is fixed on the inner surface of the casing 7 through bolts, the annular partition plate 1 and the annular cover body 2 are fixed on the lower edge plate of the guide vane 5, the upper end opening of the elbow 4 is communicated with the lower end of the guide vane 5, a cooling air flow channel is formed inside, the cooling air channel 1-2 corresponds to the air inlet side spoke end face of the wheel disc 8, the normal direction of the outlet section of the inclined groove 1-5 forms 15 degrees with the wheel disc end face, and the flowing tangential direction of the air flow flowing out of the inclined groove 1-5 is opposite to the rotating tangential direction of the wheel disc;
the annular bulge 2-2 of the annular cover body 2, the annular bulge 1-6 of the annular partition plate 1 and the annular bulge 1-7 are sequentially provided with a sealing structure with three toothed racks of the wheel disc 8; the annular groove 2-4 of the annular cover body 2 is used for placing a sealing ring 9, and the sealing ring 9 is matched with the lower part of the guide vane 5 to seal air.
The annular cooling air flow passage is connected with the inner cavity of the guide vane 5 through the bent pipe 4, and two ends of the bent pipe 4 form a tight matching surface with the guide vane 5 and the annular partition plate 1, so that air leakage is reduced.
The cooling air of the cooling system is provided by a compressor, flows into the turbine guide vane 5 through an air inlet on the surface of the turbine casing 7, is of an air core structure inside the turbine guide vane 5, flows into an annular air flow channel formed by the annular partition plate 1 and the annular cover body 2 through the bent pipe 4, and finally flows out of the cooling air channel 1-2.
The embodiment provides a be applied to marine gas turbine rim plate's cooling structure, and this structure has carried out the efficient cooling to turbine rim plate, has strengthened rim plate surface heat transfer effect, reduces rim plate temperature, the effectual atress condition that improves turbine rim plate, has increased the life-span of rim plate, has improved the reliability of unit operation.
The normal direction of the outlet section of the inclined groove 1-5 of the embodiment forms 15 degrees with the end face of the wheel disc 8, so that the flow speed of air on the surface of the wheel disc 8 is increased, and the heat exchange effect is enhanced.
The second embodiment is as follows: the first difference between this embodiment and the specific embodiment is that: the cross section of the inclined groove 1-5 is rectangular with the width of 3.4mm and the height of 4 mm. The other is the same as in the first embodiment.
And a third specific embodiment: this embodiment differs from the first or second embodiment in that: the number of the cooling air channels 1-2 is 108. The other embodiments are the same as those of the first or second embodiment.
The specific embodiment IV is as follows: the third difference between this embodiment and the third embodiment is that: the number of the bolts 3 is 42. The other is the same as in the third embodiment.
Fifth embodiment: the fourth difference between this embodiment and the third embodiment is that: the number of the air inlets 1-1 is 42. The other is the same as in the fourth embodiment.
The invention was verified with the following test:
test one: the test is a cooling structure applied to a turbine wheel disc of a marine gas turbine, as shown in fig. 3-16, and specifically comprises an annular partition plate 1, an annular cover body 2 and an elbow 4;
the annular partition plate 1 is of an annular structure, a plurality of air inlets 1-1 are uniformly formed in the side face of the annular partition plate 1, a plurality of first bolt holes 1-3 are uniformly formed in the outer edge of the inner side end face of the annular partition plate 1, a first annular bulge 1-6 and a second annular bulge 1-7 are sequentially formed in the inner side end face of the annular partition plate 1 from the first bolt holes 1-3 to the circle center direction, a plurality of oblique bulges are uniformly formed in the tail end of the first annular bulge 1-6 along the circumferential direction, and an oblique groove 1-5 is formed between the two connected oblique bulges; the normal direction of the outlet section of the inclined groove 1-5 forms 15 degrees with the end face of the wheel disc, and the tangential direction of the air flow flowing out of the inclined groove 1-5 is opposite to the tangential direction of the rotation of the wheel disc; a plurality of air outlets 1-4 are uniformly arranged between the first bolt hole 1-3 and the first annular bulge 1-6, the air outlet direction of the air outlets 1-4 is opposite to the first annular bulge 1-6, the number of the air outlets 1-4 and the number of the air inlets 1-1 are equal, and one air outlet 1-4 is communicated with one air inlet 1-1 in a one-to-one correspondence manner;
the annular cover body 2 is of an annular structure, a plurality of second bolt holes 2-1 are uniformly formed in the outer edge of the inner side end face of the annular cover body 2, the number of the second bolt holes 2-1 is the same as that of the first bolt holes 1-3, a third annular bulge 2-2 and a fourth annular bulge 2-3 are sequentially formed in the inner side end face of the annular cover body 2 from the second bolt holes 2-1 to the circle center direction, and an annular groove 2-4 is formed in the outer edge of the outer side end face of the annular cover body 2;
the outer end face of the annular cover body 2 is matched with the inner end face of the annular partition plate 1, a plurality of bolts 3 sequentially penetrate through the second bolt holes 2-1 and the first bolt holes 1-3 to fix the annular cover body 2 and the annular partition plate 1, the fourth annular bulge 2-3 is arranged outside the first annular bulge 1-6, and a cooling air channel 1-2 is formed in the area surrounded by the fourth annular bulge 2-3, the inclined groove 1-5 and the first annular bulge 1-6; one end of each bent pipe 4 is inserted into one air inlet 1-1 of the annular partition plate 1, one bent pipe 4 corresponds to one air inlet 1-1 one by one, and the other end of the bent pipe 4 is inserted into a cooling air outlet of the guide vane 5.
The application method of the cooling structure applied to the turbine wheel disc of the marine gas turbine in the test is as follows: as shown in fig. 1, the arrow is the flowing direction of cooling air, the guide vane 5 is fixed on the inner surface of the casing 7 through bolts, the annular partition plate 1 and the annular cover body 2 are fixed on the lower edge plate of the guide vane 5, the upper end opening of the elbow 4 is communicated with the lower end air outlet of the guide vane 5, a cooling air flow channel is formed inside, the cooling air channel 1-2 corresponds to the air inlet side spoke end surface of the wheel disc 8, the normal direction of the outlet section of the inclined groove 1-5 forms 15 degrees with the wheel disc end surface, and the flowing tangential direction of the air flow flowing out of the inclined groove 1-5 is opposite to the rotating tangential direction of the wheel disc; the third annular bulge 2-2 of the annular cover body 2, the annular bulge 1-6 of the annular partition plate 1 and the annular bulge 1-7 are sequentially provided with a sealing structure with three toothed racks of the wheel disc 8; the annular groove 2-4 of the annular cover body 2 is used for placing a sealing ring 9, and the sealing ring 9 is matched with the lower part of the guide vane 5 to seal air.
The annular cooling air flow passage is connected with the inner cavity of the guide vane 5 through the bent pipe 4, and two ends of the bent pipe 4 form a tight matching surface with the guide vane 5 and the annular partition plate 1, so that air leakage is reduced.
The cooling air of the cooling system is provided by a compressor, flows into the turbine guide vane 5 through an air inlet on the surface of the turbine casing 7, is of an air core structure inside the turbine guide vane 5, flows into an annular air flow channel formed by the annular partition plate 1 and the annular cover body 2 through the bent pipe 4, and finally flows out of the cooling air channel 1-2.
The test provides a cooling structure applied to a turbine wheel disc of a marine gas turbine, the structure carries out efficient cooling on the turbine wheel disc, enhances the heat exchange effect of the surface of the wheel disc, reduces the temperature of the wheel disc, effectively improves the stress condition of the turbine wheel disc, prolongs the service life of the wheel disc, and improves the running reliability of a unit.
The normal direction of the outlet section of the inclined groove 1-5 in the test forms 15 degrees with the end face of the wheel disc 8, so that the flow speed of air on the surface of the wheel disc 8 is increased, and the heat exchange effect is enhanced.
The cross section of the inclined groove 1-5 is rectangular with the width of 3.4mm and the height of 4 mm; the number of the cooling air channels 1-2 is 108; the number of the bolts 3 is 42; the number of the air inlets 1-1 is 42.
Claims (3)
1. The cooling structure applied to the turbine wheel disc of the marine gas turbine is characterized by comprising an annular partition plate (1), an annular cover body (2) and an elbow pipe (4);
the annular partition plate (1) is of an annular structure, a plurality of air inlets (1-1) are uniformly formed in the side face of the annular partition plate (1), a plurality of first bolt holes (1-3) are uniformly formed in the outer edge of the inner side end face of the annular partition plate (1), a first annular bulge (1-6) and a second annular bulge (1-7) are sequentially formed in the inner side end face of the annular partition plate (1) from the first bolt holes (1-3) to the circle center direction, a plurality of oblique bulges are uniformly formed in the tail end of the first annular bulge (1-6) along the circumferential direction, and an oblique groove (1-5) is formed between the two connected oblique bulges; the normal direction of the outlet section of the inclined groove (1-5) forms 15 degrees with the end face of the wheel disc, and the tangential direction of the air flow flowing out of the inclined groove (1-5) is opposite to the rotation tangential direction of the wheel disc; a plurality of air outlets (1-4) are uniformly arranged between the first bolt hole (1-3) and the first annular bulge (1-6), the air outlet direction of the air outlet (1-4) is opposite to the first annular bulge (1-6), the number of the air outlets (1-4) and the number of the air inlets (1-1) are equal, and one air outlet (1-4) is correspondingly communicated with one air inlet (1-1); the cross section of the inclined groove (1-5) is rectangular with the width of 3.4mm and the height of 4 mm;
the annular cover body (2) is of an annular structure, a plurality of second bolt holes (2-1) are uniformly formed in the outer edge of the inner side end face of the annular cover body (2), the number of the second bolt holes (2-1) is the same as that of the first bolt holes (1-3), a third annular bulge (2-2) and a fourth annular bulge (2-3) are sequentially formed in the inner side end face of the annular cover body (2) from the second bolt holes (2-1) to the circle center direction, and an annular groove (2-4) is formed in the outer edge of the outer side end face of the annular cover body (2);
the outer end face of the annular cover body (2) is matched with the inner end face of the annular partition plate (1), a plurality of bolts (3) sequentially penetrate through the second bolt holes (2-1) and the first bolt holes (1-3) to fix the annular cover body (2) and the annular partition plate (1), the fourth annular bulge (2-3) is arranged on the outer side of the first annular bulge (1-6), and a cooling air channel (1-2) is formed in the area surrounded by the fourth annular bulge (2-3), the inclined groove (1-5) and the first annular bulge (1-6); one end of each bent pipe (4) is inserted into one air inlet (1-1) of the annular partition plate (1), one bent pipe (4) corresponds to one air inlet (1-1) one by one, and the other end of each bent pipe (4) is inserted into a cooling air outlet of the guide vane (5); the number of the cooling air channels (1-2) is 108.
2. A cooling structure for a marine gas turbine wheel according to claim 1, characterized in that said number of bolts (3) is 42.
3. A cooling structure for a turbine wheel of a marine gas turbine according to claim 2, characterized in that said number of air inlets (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 true CN109798153B (en) | 2023-08-22 |
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| FR3101670B1 (en) * | 2019-10-08 | 2021-10-08 | Safran Aircraft Engines | Injector for a high pressure turbine |
| CN111794807B (en) * | 2020-06-24 | 2022-01-11 | 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 |
| CN112049688B (en) * | 2020-08-19 | 2021-08-10 | 西北工业大学 | Over-prerotation blade type receiving hole for equal-radius prerotation air supply system |
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