CN213421175U - Support structure for gas turbine annular combustion chamber - Google Patents
Support structure for gas turbine annular combustion chamber Download PDFInfo
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- CN213421175U CN213421175U CN202021913153.2U CN202021913153U CN213421175U CN 213421175 U CN213421175 U CN 213421175U CN 202021913153 U CN202021913153 U CN 202021913153U CN 213421175 U CN213421175 U CN 213421175U
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- combustion chamber
- ring
- guide
- annular combustion
- gas turbine
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 149
- 238000001816 cooling Methods 0.000 claims abstract description 54
- 238000007789 sealing Methods 0.000 claims description 12
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 238000005266 casting Methods 0.000 claims 1
- 230000002035 prolonged effect Effects 0.000 abstract description 5
- 238000010438 heat treatment Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
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Abstract
The utility model discloses a supporting structure of an annular combustion chamber of a gas turbine.A plurality of guide supporting tubes are uniformly arranged between the rear end of an inner cooling cylinder and the rear end of an outer cooling cylinder along the circumferential direction; the axial line of each guide support pipe is in the radial direction of the outer ring of the annular combustion chamber; the outer end of the guide supporting tube is fixed at the rear end of the outer cooling cylinder, and the inner end of the guide supporting tube is fixed at the rear end of the inner cooling cylinder; the exhaust pipe is uniformly fixed with guide supporting seats along the circumferential direction corresponding to the plurality of guide supporting pipes; each guide support seat is fixedly provided with a guide pin along the radial direction; each guide pin is inserted into a corresponding guide support tube. The utility model discloses a supporting structure of gas turbine annular combustion chamber not only can satisfy and support the combustion chamber basically, can also evenly guide the thermal energy of combustion chamber, guarantees that the central axis does not take place radial offset after whole combustion chamber is heated the inflation to guaranteed the axiality of parts such as combustion chamber and combustion chamber nozzle, prolonged the life of junctions such as combustion chamber, nozzle, machine casket, and simple structure, the good reliability.
Description
Technical Field
The utility model relates to a gas turbine, in particular to bearing structure of gas turbine annular combustion chamber.
Background
A Gas Turbine (Gas Turbine) is a rotary power machine which uses continuously flowing Gas as a working medium and converts the heat energy of the working medium into mechanical work. The combustion chamber is used as an important part of the gas turbine, is influenced by a large temperature when the heat energy of the working medium is converted, and the axial centering of the combustion chamber is influenced by the instability of the thermal expansion of the combustion chamber; when the central axis of the combustion chamber is offset, the coaxiality of the combustion chamber with the combustion chamber nozzle, the casing, the rotor wheel and the like is seriously affected. Because a rotor impeller, a combustion chamber, a nozzle and the like in the gas turbine need to have high coaxiality requirements, when the central axis of the combustion chamber is axially offset, internal components of the gas turbine are subjected to offset load, if the offset load is too large, the internal components are deformed and failed, internal interference is seriously and directly caused, the gas turbine is directly scrapped, and the service life of the gas turbine is seriously influenced.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide a bearing structure of gas turbine annular combustion chamber, not only can satisfy and support the combustion chamber basically, can also evenly guide the thermal energy of combustion chamber, guarantee that the central axis does not take place radial offset after whole combustion chamber is heated the inflation to guaranteed the axiality of parts such as combustion chamber and combustion chamber nozzle, prolonged the life of junctions such as combustion chamber, nozzle, machine casket, and simple structure, the good reliability.
In order to solve the technical problem, the utility model provides a supporting structure of an annular combustion chamber of a gas turbine, the annular combustion chamber of the gas turbine comprises an annular combustion chamber outer ring 1, an annular combustion chamber inner ring 2, an exhaust pipe 4, an inner cooling cylinder 32 and an outer cooling cylinder 31 which are coaxially arranged; the annular combustion chamber outer ring 1 is sleeved outside the annular combustion chamber inner ring 2, and the rear ends of the annular combustion chamber outer ring 1 and the annular combustion chamber inner ring 2 are connected together; the exhaust pipe 4 is sleeved on the inner side of the annular combustion chamber inner ring 2; the front end of the exhaust pipe 4 is connected with the front end of the annular combustion chamber inner ring 2; an outer cooling cylinder 31 is sleeved on the periphery of the outer ring 1 of the annular combustion chamber; an inner cooling cylinder 32 is sleeved on the inner circumference of the annular combustion chamber inner ring 2; n guide support pipes 41 are uniformly arranged between the rear end of the inner cooling cylinder 32 and the rear end of the outer cooling cylinder 31 along the circumferential direction, wherein N is an integer greater than 2;
the axes of the guide support pipes 41 are in the radial direction of the annular combustion chamber outer ring 1;
the outer end of the guide support tube 41 is fixed at the rear end of the outer cooling cylinder 31, and the inner end is fixed at the rear end of the inner cooling cylinder 32;
n guide supporting seats 43 are uniformly fixed on the exhaust pipe 4 along the circumferential direction corresponding to the N guide supporting pipes 41;
each guide support seat 43 is fixedly provided with a guide pin 42 along the radial direction;
each guide pin 42 is inserted into the corresponding guide support tube 41.
Preferably, the rear end of the annular combustion chamber outer ring 1 is directly welded and fixed with the rear part of the outer cooling cylinder 31;
the rear end of the outer cooling cylinder 31 extends out to the rear side of the rear end of the annular combustion chamber outer ring 1;
the rear end of the annular combustion chamber inner ring 2 is welded and connected with the rear end of the inner cooling cylinder 32 through an inner connecting ring 81;
the guide support tube 41 has an outer end fixed to the rear end of the outer cooling cylinder 31 and an inner end fixed to the inner collar 81.
Preferably, the front end of the outer cooling cylinder 31 is welded and fixed with the front part of the annular combustion chamber outer ring 1 through an outer connecting ring 82;
the front end of the inner cooling cylinder 32 is welded and fixed with the front part of the annular combustion chamber inner ring 2 through an inner connecting ring 81.
Preferably, the cross section of the inner connecting ring 81 or the outer connecting ring 82 is "C" shaped.
Preferably, the near inner cooling cylinder part or the middle part of the guide support tube 41 is a matching area;
the inner diameter of the matching area of the guide support tube 41 is 1-1.05 times of the outer diameter of the guide pin 42;
the inner diameter of the part outside the matching area of the guide support tube 41 is 1.06-1.2 times of the outer diameter of the guide pin 42.
Preferably, b > 3R;
b is the length of the fitting area of the guide support tube 41, and R is the outer diameter of the guide pin 42;
at normal temperature, the outer end of the guide pin 42 is inserted outside the fitting area of the guide support tube 41.
Preferably, the exhaust pipe 4 is uniformly welded and fixed with N guide support seats 43 along the circumferential direction corresponding to the N guide support tubes 41.
Preferably, the casing shell 51 is arranged outside the annular combustion chamber outer ring 1;
a plurality of combustion chamber lifting lugs 22 are uniformly arranged at the front end of the annular combustion chamber outer ring 1 along the circumferential direction;
the respective combustion chamber lugs 22 are fixed to the casing shell 51 by positioning bolts 21, respectively.
Preferably, the combustion chamber lifting lug 22 at the front end of the annular combustion chamber outer ring 1 is integrally cast.
Preferably, the rear end of the exhaust pipe 4 is welded to the rear of the casing 51 through the nozzle support ring 25.
Preferably, the gas turbine annular combustor further comprises a combustor nozzle ring 6;
the combustion chamber nozzle ring 6 comprises an outer nozzle ring 61 and an inner nozzle ring 62;
the front part of the outer nozzle ring 61 is bent inwards along the radial direction, and the rear part is bent backwards along the axial direction;
the front part of the inner nozzle ring 62 is bent outwards along the radial direction, and the rear part is bent backwards along the axial direction;
the inner nozzle ring 62 and the outer nozzle ring 61 form a hot gas injection channel;
the front end of the outer ring 1 of the annular combustion chamber is connected with the rear end of the outer nozzle ring 61 in a sealing fit manner;
the front end of the exhaust pipe 4 is connected with the rear end of the inner nozzle ring 62 in a sealing fit manner.
Preferably, the exhaust pipe 4 is connected at its forward end to the inner nozzle ring 62 at its rearward end in sealing engagement by an inner piston ring 94.
Preferably, the front end of the outer ring 1 of the annular combustion chamber is connected with the rear end of the outer nozzle ring 61 in a sealing fit manner through an outer piston ring.
The utility model discloses a bearing structure of gas turbine annular combustion chamber adopts the direction to support, and uide pin 42 passes through the direction stay tube 41 and the direction supporting seat 43 is connected combustion chamber and blast pipe 4, and the cover of direction stay tube 41 is outside uide pin 41, and the heat expansion of guide combustion chamber keeps the axiality of gas turbine internals when guaranteeing the even directional inflation of combustion chamber, extension gas turbine life. This supporting structure of gas turbine annular combustion chamber not only can satisfy and support the combustion chamber basically, can also evenly guide the thermal energy of combustion chamber, guarantees that the central axis does not take place radial offset after whole combustion chamber is heated the inflation to guarantee the axiality of parts such as combustion chamber and combustion chamber nozzle, prolonged the life of junctions such as combustion chamber, nozzle, quick-witted casket, and simple structure, the good reliability.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings required for the present invention are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a cross-sectional view of an embodiment of a support structure for an annular combustor of a gas turbine according to the present invention;
FIG. 2 is a rear perspective view of an embodiment of a support structure for an annular combustor of a gas turbine according to the present invention;
FIG. 3 is a rear cross-sectional view of an embodiment of a support structure for an annular combustor of a gas turbine according to the present invention;
FIG. 4 is a schematic view of a guiding support structure according to an embodiment of the support structure of the gas turbine annular combustor of the present invention;
FIG. 5 is an enlarged view of a guide support structure of an embodiment of the support structure of the gas turbine annular combustor of the present invention;
fig. 6 is a front perspective view of an embodiment of a support structure for an annular combustor of a gas turbine according to the present invention.
Description of reference numerals:
1, an annular combustor outer ring; 2, an annular combustion chamber inner ring; 4, exhausting the pipe; 31 an outer cooling cylinder; 32, cooling the barrel; 41 guiding and supporting the tube; 42 a guide pin; 43 guiding the supporting seat; 81 inner connecting rings; 82 an outer connecting ring; 51 a case housing; 21 positioning bolts; 22 combustion chamber lifting lugs; 25 nozzle support rings; 6, a nozzle ring of the combustion chamber; 61 outer nozzle ring; 62 an inner nozzle ring; 94 inner piston ring.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments, but not all embodiments, of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
Example one
The supporting structure of the gas turbine annular combustion chamber is shown in fig. 1, and the gas turbine annular combustion chamber comprises an annular combustion chamber outer ring 1, an annular combustion chamber inner ring 2, an exhaust pipe 4, an inner cooling cylinder 32 and an outer cooling cylinder 31 which are coaxially arranged;
the annular combustion chamber outer ring 1 is sleeved outside the annular combustion chamber inner ring 2, and the rear ends of the annular combustion chamber outer ring 1 and the annular combustion chamber inner ring 2 are connected together;
the exhaust pipe 4 is sleeved on the inner side of the annular combustion chamber inner ring 2;
the front end of the exhaust pipe 4 is connected with the front end of the annular combustion chamber inner ring 2;
an outer cooling cylinder 31 is sleeved on the periphery of the outer ring 1 of the annular combustion chamber;
an inner cooling cylinder 32 is sleeved on the inner circumference of the annular combustion chamber inner ring 2;
n guide support pipes 41 are uniformly arranged between the rear end of the inner cooling cylinder 32 and the rear end of the outer cooling cylinder 31 along the circumferential direction, wherein N is an integer greater than 2;
the axes of the guide support pipes 41 are in the radial direction of the annular combustion chamber outer ring 1;
the outer end of the guide support tube 41 is fixed at the rear end of the outer cooling cylinder 31, and the inner end is fixed at the rear end of the inner cooling cylinder 32;
n guide supporting seats 43 are uniformly fixed on the exhaust pipe 4 along the circumferential direction corresponding to the N guide supporting pipes 41;
each guide support seat 43 is fixedly provided with a guide pin 42 along the radial direction;
each guide pin 42 is inserted into the corresponding guide support tube 41.
The supporting structure of the annular combustion chamber of the gas turbine in the first embodiment adopts guide support, the guide pin 42 connects the combustion chamber and the exhaust pipe 4 through the guide support pipe 41 and the guide support seat 43, the guide support pipe 41 is sleeved outside the guide pin 41 to guide the thermal expansion of the combustion chamber, the coaxiality of internal components of the gas turbine is kept while the uniform directional expansion of the combustion chamber is ensured, and the service life of the gas turbine is prolonged. This supporting structure of gas turbine annular combustion chamber not only can satisfy and support the combustion chamber basically, can also evenly guide the thermal energy of combustion chamber, guarantees that the central axis does not take place radial offset after whole combustion chamber is heated the inflation to guarantee the axiality of parts such as combustion chamber and combustion chamber nozzle, prolonged the life of junctions such as combustion chamber, nozzle, quick-witted casket, and simple structure, the good reliability.
Example two
Based on the supporting structure of the annular combustion chamber of the gas turbine in the first embodiment, the rear end of the outer ring 1 of the annular combustion chamber is directly welded and fixed with the rear part of the outer cooling cylinder 31;
the rear end of the outer cooling cylinder 31 extends out to the rear side of the rear end of the annular combustion chamber outer ring 1;
the rear end of the annular combustion chamber inner ring 2 is welded and connected with the rear end of the inner cooling cylinder 32 through an inner connecting ring 81;
the guide support tube 41 has an outer end fixed to the rear end of the outer cooling cylinder 31 and an inner end fixed to the inner collar 81.
Preferably, the front end of the outer cooling cylinder 31 is welded and fixed with the front part of the annular combustion chamber outer ring 1 through an outer connecting ring 82;
the front end of the inner cooling cylinder 32 is welded and fixed with the front part of the annular combustion chamber inner ring 2 through an inner connecting ring 81.
Preferably, the cross section of the inner connecting ring 81 or the outer connecting ring 82 is "C" shaped.
Preferably, the exhaust pipe 4 is uniformly welded and fixed with N guide support seats 43 along the circumferential direction corresponding to the N guide support tubes 41.
In the supporting structure of the annular combustor of the gas turbine according to the second embodiment, both ends of the guide support tube 41 are welded to the outer cooling cylinder 23 and the inner connection ring 81 so as to be fixed to the combustor.
EXAMPLE III
Based on the supporting structure of the annular combustion chamber of the gas turbine in the first embodiment, the near inner cooling cylinder part or the middle part of the guide supporting pipe 41 is a matching area;
the inner diameter of the matching area of the guide support tube 41 is 1-1.05 times of the outer diameter of the guide pin 42;
the inner diameter of the part outside the matching area of the guide support tube 41 is 1.06-1.2 times of the outer diameter of the guide pin 42.
Preferably, b > 3R;
b is the length of the fitting area of the guide support tube 41, and R is the outer diameter of the guide pin 42;
at normal temperature, the outer end of the guide pin 42 is inserted outside the fitting area of the guide support tube 41.
In the support structure of the annular combustion chamber of the gas turbine according to the third embodiment, assuming that the normal center of the joint of the guide support tube 41 and the outer cooling cylinder 32 is counted as the pivot a, the intersection point of the axial direction of the guide support tube 41 and the axial direction of the combustion chamber is counted as the center point O, under the action of the guide pin 42, the annular combustion chamber outer ring 1 and the annular combustion chamber inner ring 2 expand uniformly by heating along the axial direction of the guide pin 42, assuming that the radial unilateral expansion amount of the annular combustion chamber outer ring 1 after being expanded by heating is a, the reserved length of the matching surface of the guide pin 42 and the guide support tube 41 is the matching region length b of the guide support tube 41, assuming that the normal center of the joint of the guide support tube 41 and the outer cooling cylinder 32 after being expanded by heating the annular combustion chamber outer ring 1 changes from the point a to the point a', and calculating the expansion.
Example four
Based on the supporting structure of the gas turbine annular combustor of the first embodiment, the casing shell 51 is arranged outside the annular combustor outer ring 1;
a plurality of combustion chamber lifting lugs 22 are uniformly arranged at the front end of the annular combustion chamber outer ring 1 along the circumferential direction;
the respective combustion chamber lugs 22 are fixed to the casing shell 51 by positioning bolts 21, respectively.
Preferably, the combustion chamber lifting lug 22 at the front end of the annular combustion chamber outer ring 1 is integrally cast.
Preferably, the rear end of the exhaust pipe 4 is welded to the rear of the casing 51 through the nozzle support ring 25.
In the support structure of the annular combustion chamber of the gas turbine according to the fourth embodiment, the combustion chamber lifting lugs 22 are uniformly arranged at the front end of the outer ring 1 of the annular combustion chamber, and the plurality of combustion chamber lifting lugs 22 and the positioning bolts corresponding to the positioning bolts 21 which are uniformly distributed determine the axial and radial positions of the combustion chamber.
EXAMPLE five
Based on the supporting structure of the gas turbine annular combustion chamber of the first embodiment, the gas turbine annular combustion chamber further comprises a combustion chamber nozzle ring 6;
the combustion chamber nozzle ring 6 comprises an outer nozzle ring 61 and an inner nozzle ring 62;
the front part of the outer nozzle ring 61 is bent inwards along the radial direction, and the rear part is bent backwards along the axial direction;
the front part of the inner nozzle ring 62 is bent outwards along the radial direction, and the rear part is bent backwards along the axial direction;
the inner nozzle ring 62 and the outer nozzle ring 61 form a hot gas injection channel;
the front end of the outer ring 1 of the annular combustion chamber is connected with the rear end of the outer nozzle ring 61 in a sealing fit manner;
the front end of the exhaust pipe 4 is connected with the rear end of the inner nozzle ring 62 in a sealing fit manner.
Preferably, the exhaust pipe 4 is connected at its forward end to the inner nozzle ring 62 at its rearward end in sealing engagement by an inner piston ring 94.
Preferably, the front end of the outer ring 1 of the annular combustion chamber is connected with the rear end of the outer nozzle ring 61 in a sealing fit manner through an outer piston ring.
The above are merely preferred embodiments of the present application and are not intended to limit the present application. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (13)
1. A supporting structure of an annular combustion chamber of a gas turbine comprises an outer annular combustion chamber ring (1), an inner annular combustion chamber ring (2), an exhaust pipe (4), an inner cooling cylinder (32) and an outer cooling cylinder (31) which are coaxially arranged; the annular combustion chamber outer ring (1) is sleeved outside the annular combustion chamber inner ring (2), and the rear ends of the annular combustion chamber outer ring and the annular combustion chamber inner ring are connected together; the exhaust pipe (4) is sleeved on the inner side of the annular combustion chamber inner ring (2); the front end of the exhaust pipe (4) is connected with the front end of the annular combustion chamber inner ring (2); an outer cooling cylinder (31) is sleeved on the periphery of the outer ring (1) of the annular combustion chamber; an inner cooling cylinder (32) is sleeved on the inner circumference of the annular combustion chamber inner ring (2); the device is characterized in that N guide support pipes (41) are uniformly arranged between the rear end of the inner cooling cylinder (32) and the rear end of the outer cooling cylinder (31) along the circumferential direction, and N is an integer greater than 2;
the axes of the guide support pipes (41) are in the radial direction of the outer ring (1) of the annular combustion chamber;
the outer end of the guide support tube (41) is fixed at the rear end of the outer cooling cylinder (31), and the inner end of the guide support tube is fixed at the rear end of the inner cooling cylinder (32);
n guide supporting seats (43) are uniformly fixed on the exhaust pipe (4) along the circumferential direction corresponding to the N guide supporting pipes (41);
each guide support seat (43) is fixedly provided with a guide pin (42) along the radial direction;
each guide pin (42) is inserted into a corresponding guide support tube (41).
2. The gas turbine annular combustor support structure as claimed in claim 1,
the rear end of the outer ring (1) of the annular combustion chamber is directly welded and fixed with the rear part of the outer cooling cylinder (31);
the rear end of the outer cooling cylinder (31) protrudes to the rear side of the rear end of the annular combustion chamber outer ring (1);
the rear end of the annular combustion chamber inner ring (2) is welded and connected with the rear end of the inner cooling cylinder (32) through an inner connecting ring (81);
the outer end of the guide support pipe (41) is fixed at the rear end of the outer cooling cylinder (31), and the inner end is fixed to the inner connecting ring (81).
3. The gas turbine annular combustor support structure as claimed in claim 2,
the front end of the outer cooling cylinder (31) is welded and fixed with the front part of the annular combustion chamber outer ring (1) through an outer connecting ring (82);
the front end of the inner cooling cylinder (32) is welded and fixed with the front part of the annular combustion chamber inner ring (2) through an inner connecting ring (81).
4. The gas turbine annular combustor support structure as claimed in claim 3,
the cross section of the inner connecting ring (81) or the outer connecting ring (82) is C-shaped.
5. The gas turbine annular combustor support structure as claimed in claim 1,
the near inner cooling cylinder part or the middle part of the guide support tube (41) is a matching area;
the inner diameter of the matching area of the guide support tube (41) is 1-1.05 times of the outer diameter of the guide pin (42);
the inner diameter of the part outside the matching area of the guide support tube (41) is 1.06-1.2 times of the outer diameter of the guide pin (42).
6. The gas turbine annular combustor support structure as claimed in claim 1,
b>3R；
b is the length of the matching area of the guide support tube (41), and R is the outer diameter of the guide pin (42);
at normal temperature, the outer end of the guide pin (42) is inserted outside the matching area of the guide support tube (41).
7. The gas turbine annular combustor support structure as claimed in claim 1,
the exhaust pipe (4) is uniformly welded and fixed with N guide supporting seats (43) along the circumferential direction corresponding to the N guide supporting pipes (41).
8. The gas turbine annular combustor support structure as claimed in claim 1,
the casing shell (51) is arranged outside the annular combustion chamber outer ring (1);
a plurality of combustion chamber lifting lugs (22) are uniformly arranged at the front end of the annular combustion chamber outer ring (1) along the circumferential direction;
the combustion chamber lugs (22) are respectively fixed to the casing shell (51) through positioning bolts (21).
9. The gas turbine annular combustor support structure of claim 8,
the combustion chamber lifting lug (22) at the front end of the annular combustion chamber outer ring (1) is formed by integral casting.
10. The gas turbine annular combustor support structure of claim 8,
the rear end of the exhaust pipe (4) is welded with the rear part of the casing shell (51) into a whole through a nozzle support ring (25).
11. The gas turbine annular combustor support structure as claimed in claim 1,
the gas turbine annular combustion chamber also comprises a combustion chamber nozzle ring (6);
the combustion chamber nozzle ring (6) comprises an outer nozzle ring (61) and an inner nozzle ring (62);
the front part of the outer nozzle ring (61) is bent inwards along the radial direction, and the rear part is bent backwards along the axial direction;
the front part of the inner nozzle ring (62) is bent outwards along the radial direction, and the rear part is bent backwards along the axial direction;
the inner nozzle ring (62) and the outer nozzle ring (61) form a hot gas injection channel;
the front end of the outer ring (1) of the annular combustion chamber is connected with the rear end of the outer nozzle ring (61) in a sealing fit manner;
the front end of the exhaust pipe (4) is connected with the rear end of the inner nozzle ring (62) in a sealing fit manner.
12. The gas turbine annular combustor support structure of claim 11,
the front end of the exhaust pipe (4) is connected with the rear end of the inner nozzle ring (62) in a sealing fit mode through an inner piston ring (94).
13. The gas turbine annular combustor support structure of claim 11,
the front end of the outer ring (1) of the annular combustion chamber is connected with the rear end of the outer nozzle ring (61) in a sealing fit manner through an outer piston ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021913153.2U CN213421175U (en) | 2020-09-04 | 2020-09-04 | Support structure for gas turbine annular combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021913153.2U CN213421175U (en) | 2020-09-04 | 2020-09-04 | Support structure for gas turbine annular combustion chamber |
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| Publication Number | Publication Date |
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| CN213421175U true CN213421175U (en) | 2021-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202021913153.2U Active CN213421175U (en) | 2020-09-04 | 2020-09-04 | Support structure for gas turbine annular combustion chamber |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165815A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Pull rod device for compensating thermal deformation |
-
2020
- 2020-09-04 CN CN202021913153.2U patent/CN213421175U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165815A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Pull rod device for compensating thermal deformation |
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