CN112761743B - Gas turbine exhaust diffuser seal structure - Google Patents
Gas turbine exhaust diffuser seal structure Download PDFInfo
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- CN112761743B CN112761743B CN202011588349.3A CN202011588349A CN112761743B CN 112761743 B CN112761743 B CN 112761743B CN 202011588349 A CN202011588349 A CN 202011588349A CN 112761743 B CN112761743 B CN 112761743B
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- spring
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- diffuser
- sealing ring
- inner ring
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a sealing structure of an exhaust diffuser of a gas turbine, which belongs to the field of gas turbines.A mounting groove is arranged on one of an inner ring of a front-section diffuser and an inner ring of a rear-section diffuser, the mounting groove is arranged on the matching surface of the inner ring of the front-section diffuser and the inner ring of the rear-section diffuser, the sealing ring is partially positioned in the mounting groove, a first spring is arranged on the side surface of the mounting groove, the first spring pushes the sealing ring out towards the pressure direction of gas generated to the sealing ring, a second spring is arranged at the bottom of the mounting groove, and the second spring pushes the sealing ring out of the mounting groove, so that the sealing ring is tightly pressed on the matching surface of the inner ring of the front-section diffuser and the inner ring of the rear-section diffuser and the side wall of the mounting groove; the stability of the sealing structure is further improved through structures such as the spring sleeve and the like; simple structure and low cost.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a gas turbine exhaust diffuser sealing structure.
Background
In an industrial gas turbine, the exhaust speed of a turbine is high, which causes great exhaust loss and affects the unit efficiency, in order to reduce the loss, the exhaust speed must be reduced, therefore, a diffuser is arranged on the exhaust side of the turbine, generally, the diffuser is an annular channel formed by an inner ring and an outer ring, the axial span is large, in addition, a tangential support, an oil pipe, an air pipe and the like all need to pass through the diffuser to reach a rear bearing seat, in order to facilitate installation and reduce the axial span, the diffuser is designed into a two-section structure in the axial direction, and a sealing structure is arranged at a connecting part to prevent gas leakage. If gas leaks from the inner ring position, the gas directly reaches the bearing seat position, and if the temperature of the bearing rises, the bearing is damaged, and if lubricating oil seeps out, fire is caused. Therefore, the tightness of the joint between the front and rear sections of the diffuser should be strictly ensured.
Fig. 1 is a schematic view showing a diffuser structure according to the prior art, and fig. 2 is an enlarged view of a portion a according to the prior art. The supporting plate 2 penetrates through the cylinder 1, the front diffuser outer ring 3 and the front diffuser inner ring 5 to be connected with a bearing seat 7, and is used for supporting a bearing of the gas turbine; the front section diffuser outer ring 3 and the rear section diffuser outer ring 4 form a diffuser outer ring, and the front section diffuser inner ring 5 and the rear section diffuser inner ring 6 form a diffuser inner ring; the junction of the front diffuser inner ring 5 and the rear diffuser inner ring 6 is provided with a diffuser sealing structure, as shown in fig. 2, a sealing groove 8 is arranged on the front diffuser inner ring 5 or the rear diffuser inner ring 6, a sealing ring 9 is arranged in the sealing groove 8, and the connection structure of the front diffuser inner ring 5 and the rear diffuser inner ring 6 is sealed through the sealing ring 9 so as to prevent the bearing damage caused by the leakage of gas and lubricating oil.
However, the above prior art solutions have the following problems: the diffuser wall is thinner than the cylinder 1, and therefore is more likely to deform when exposed to a higher temperature environment, and may deform by a greater amount than the cylinder. Because the diameter of the diffuser is large and the front section and the rear section are of a splicing structure, when the peripheral direction is unevenly heated, the deformation amount is different, the sealing ring is easy to displace, and the sealing structure is easy to lose efficacy. In addition, during the operation of the unit, due to the influence of factors such as vibration, sealing failure may be caused, gas leakage is caused, and the safe operation of the unit is influenced.
In view of the above problem, document CN109630218A discloses an exhaust member of a gas turbine, provided with an inner diffuser formed in a cylindrical shape and divided into a plurality of segments in a circumferential direction; a 1 st seal case formed in a cylindrical shape and integrally configured in a circumferential direction, a front end portion of which is coupled to a rear end portion of the inner diffuser; a 2 nd hermetic case formed in a cylindrical shape and integrally configured in a circumferential direction, a front end portion being coupled to a rear end portion of the 1 st hermetic case; and a support coupling portion that supports the rear end portion of the 1 st seal housing and the front end portion of the 2 nd seal housing so as to be movable in the axial direction. Thereby, the housing can be easily removed and mounted, and the maintainability can be improved. However, the sealing structure can only deal with the axial movement between the 1 st sealing shell and the 2 nd sealing shell, and when the two move radially, the sealing structure has certain sealing failure risks.
Document CN104040148A discloses a gas turbine including a strut that penetrates an outer diffuser and an inner diffuser to connect an exhaust chamber wall and a bearing housing; a pillar cover that covers the pillar along an extending direction of the pillar; a partition wall that is disposed between a radially inner side of the inner diffuser and a radially outer side of the bearing housing, seals between the upstream side portion and the bearing housing, seals between the downstream side portion and the inner diffuser, and has a strut through-hole through which a strut passes; and a hole sealing member fixed to the pillar through-hole of the partition wall so as to be movable relative to the pillar in the extending direction, the hole sealing member closing a gap between the pillar through-hole and the pillar. This document describes a seal member that is pressed against a seal body by a spring so as to press the seal body against an inner wall of an inner diffuser, thereby ensuring that the seal state is maintained even when the equipment is displaced in the axial and radial directions due to thermal expansion of cooling gas during operation of the gas turbine. However, in the above technical solution, the axial movement is handled by sliding the sealing body on the inner diffusion wall, and the sealing body moves between the two side walls of the groove where the sealing body is located during sliding, and cannot be pressed against the side walls, so that gas is likely to enter the space near the bearing housing from the gap between the sealing body and the groove where the sealing body is located, and there is a risk of sealing failure.
Disclosure of Invention
Aiming at the problem that sealing failure is easily caused when a sealing structure in the prior art slides, the invention provides a sealing structure of an exhaust diffuser of a gas turbine.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows: the utility model provides a gas turbine exhaust diffuser seal structure, includes anterior segment diffuser inner ring, back end diffuser inner ring, sealing ring, first spring, second spring, anterior segment diffuser inner ring with back end diffuser inner ring cooperatees its characterized in that: the gas-gas burner is characterized in that one of the front-section diffuser inner ring and the rear-section diffuser inner ring is provided with a mounting groove, the mounting groove is formed in the matching surface of the front-section diffuser inner ring and the rear-section diffuser inner ring, the sealing ring is partially located in the mounting groove, the side face of the mounting groove is provided with the first spring, the first spring enables the sealing ring to eject gas in the direction of pressure generated by the sealing ring, the bottom of the mounting groove is provided with the second spring, and the second spring enables the sealing ring to eject out of the mounting groove.
Preferably, a first hole for accommodating the first spring and a second hole for accommodating the second spring are arranged on the sealing ring, and the first hole and the second hole are both blind holes.
Preferably, the first and second holes on the sealing ring are arranged in a staggered manner.
Preferably, one side of the first spring, which is far away from the first hole, and one side of the second spring, which is far away from the second hole, are respectively sleeved with a spring sleeve.
Preferably, a part of the spring housing sleeved on the first spring on one side of the opening is located in the first hole, and a part of the spring housing sleeved on the second spring on one side of the opening is located in the second hole.
Preferably, a through hole is drilled at the bottom of the spring sleeve, an opening is arranged on the side face of the spring sleeve, and the opening is communicated with the through hole.
Preferably, the sealing ring is formed by combining a plurality of identical sealing ring monomers.
Preferably, the two ends of the single sealing ring are respectively provided with a first sealing extending section and a second sealing extending section, and the first sealing extending section and the second sealing extending section are overlapped in sequence.
Preferably, the sealing structure further comprises a sealing groove and a sealing ring, the cross section of the sealing groove is trapezoidal, the width of the groove bottom of the trapezoidal groove is smaller than that of the groove opening of the trapezoidal groove, and the cross section of the sealing ring is trapezoidal matched with the sealing groove.
Preferably, the number of the seal grooves is multiple, a gap is reserved between the seal grooves, and the number of the seal rings is the same as that of the seal grooves.
The invention has the following beneficial effects: the sealing ring is pressed on the side wall of the sealing groove and the matching surface through the first spring and the second spring, and can still be pressed on the contact surface when the sealing ring slides with the contact surface, so that the risk of failure of the sealing structure when the sealing structure slides relative to the contact surface is reduced; the sealing structure of the exhaust diffuser is simple and easy to realize, the sealing of the inner rings of the front-section diffuser and the rear-section diffuser is realized by mounting the sealing ring on the inner ring of the rear-section diffuser, the improvement cost of the existing equipment is reduced, meanwhile, the leakage can be effectively reduced, and the safe operation of a unit is ensured; the disassembly and assembly are convenient, and the maintainability of the unit is improved.
Drawings
Fig. 1 is a schematic view of an exhaust diffuser according to the prior art.
Fig. 2 is an enlarged view of a portion a of the prior art.
FIG. 3 is a schematic view of an exhaust diffuser sealing structure of a gas turbine exhaust diffuser sealing structure.
FIG. 4 is an enlarged view of section B of a gas turbine exhaust diffuser seal configuration.
FIG. 5 is an elevation view of a spring pocket of a gas turbine exhaust diffuser seal structure.
Figure 6 is a C-C cross-sectional view of the spring housing.
FIG. 7 is a schematic view of a single seal ring structure of a gas turbine exhaust diffuser seal structure.
FIG. 8 is a schematic view of a seal ring assembly for a gas turbine exhaust diffuser seal structure.
In the figure: 1 is the cylinder, 2 is the backup pad, 3 is the anterior segment diffuser outer loop, 4 is the back end diffuser outer loop, 5 is the anterior segment diffuser inner loop, 6 is the back end diffuser inner loop, 7 is the bearing frame, 8 is the seal groove, 9 is the sealing washer, 10 is the first hole, 11 is first spring, 12 is the spring housing, 1201 is the first spring housing, 1202 is the second spring housing, 13 is the second hole, 14 is the second spring, 15 is the mounting groove, 16 is the sealing ring, 17 is the sealing ring monomer, 17a is the 1 st sealing ring monomer, 17b is the 2 nd sealing ring monomer, 18 is the first sealed section that stretches out, 19 is the sealed section that stretches out of second.
Detailed Description
The invention will be further described with reference to the following detailed description of the drawings. The invention only aims at the sealing structure at the tail end of the diffuser, and does not relate to the structure and installation and fixation of the diffuser.
In the description of the present invention, it should be noted that terms indicating orientation or positional relationship such as "upper", "lower", "left", "right", and the like are based on the orientation or positional relationship shown in the drawings, and are only for the purpose of simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, a specific orientation configuration or operation, and thus, should not be construed as limiting the present invention. Furthermore, any combination of the various embodiments or technical features described below may be used to form new embodiments without conflict.
In the description of the present invention, the axial direction refers to the left and right directions in the drawings; radial refers to the up and down direction in the figure. In addition, the drawings only schematically illustrate the sealing structure at the tail end of the exhaust diffuser and the position of the sealing structure, but the sealing structure does not limit the sealing structure scheme of the exhaust diffuser of the gas turbine.
As shown in fig. 3 and 4, the sealing structure of the gas turbine exhaust diffuser includes a front diffuser inner ring 5, a rear diffuser inner ring 6, a sealing ring 16, a first spring 11, and a second spring 14, wherein the front diffuser inner ring 5 is matched with the rear diffuser inner ring 6, and is characterized in that: one of anterior segment diffuser inner ring 5 and back end diffuser inner ring 6 is provided with mounting groove 15, mounting groove 15 sets up on the fitting surface of anterior segment diffuser inner ring 5 and back end diffuser inner ring 6, sealing ring 16 part is arranged in mounting groove 15, be provided with first spring 11 on the side of mounting groove 15, first spring 11 is ejecting to the pressure direction that gas produced sealing ring 16 with sealing ring 16, the tank bottom of mounting groove 15 is provided with second spring 14, second spring 14 is ejecting mounting groove 15 with sealing ring 16. In this embodiment, the mounting groove 15 is provided on the rear diffuser inner ring 6, the first spring 11 pushes out the seal ring 16 toward the bearing, so that the seal ring 16 is pressed against the side surface of the mounting groove 15 close to the bearing, and the second spring 14 pushes out the seal ring 16 from the mounting groove 15 and presses the seal ring 16 against the front diffuser inner ring 5.
The principle of the present invention will be explained by taking this embodiment as an example: when the exhaust diffuser works, gas flows from the front-stage diffuser to the rear-stage diffuser through the annular channel between the outer ring of the diffuser and the inner ring of the diffuser, the pressure of the gas in the annular channel is higher, and pressure in the direction of the bearing is generated on the sealing ring 16 through the gap between the inner ring 5 of the front-stage diffuser and the inner ring 6 of the rear-stage diffuser. The second spring 14 presses the sealing ring 16 against the inner ring 5 of the front diffuser, so that the gas in the annular channel is prevented from entering the space near the bearing seat 7; the first spring 11 presses the sealing ring 16 against the side wall of the mounting groove 15 to prevent the gas in the annular channel from entering the space near the bearing seat 7 from the side wall of the mounting groove 15; meanwhile, the gas pressure and the pressure generated by the first spring 11 are both towards the bearing direction, so that the sealing ring 16 is further pressed on the side wall of the mounting groove 15, and the sealing effect of the sealing ring 16 is improved. When axial displacement appears between the front diffuser inner ring 5 and the rear diffuser inner ring 6, the sealing ring 16 is still pressed on the front diffuser inner ring 5 under the action of the elastic force of the first spring 11, so that the sealing ring 17 can still realize sealing. When radial displacement occurs between the front diffuser inner ring 5 and the rear diffuser inner ring 6, the sealing ring 16 is still pressed on the side wall of the mounting groove 15 under the action of the elastic force of the second spring 14, so that the sealing ring 16 keeps sealing. When the sealing structure is influenced by the vibration of the front-section diffuser inner ring 5 and the rear-section diffuser inner ring 6, the sealing structure is always pressed on the side wall of the mounting groove 15 and the front-section diffuser inner ring 5 through the elastic forces of the first spring 11 and the second spring 14, and sealing is realized. By the mode, the sealing structure can still keep sealing when axial and radial displacement and vibration occur between the front-section diffuser inner ring 5 and the rear-section diffuser inner ring 6, and the combined action of radial sealing and axial sealing is realized; meanwhile, when the sealing ring 16 slides with the contact surface of the sealing ring, the sealing ring 16 is kept in a compression state with the contact surface, and the sealing structure is prevented from losing efficacy during sliding.
As shown in fig. 4, the sealing ring 16 is provided with a first hole 10 for accommodating the first spring 11 and a second hole 13 for accommodating the second spring 14, and both the first hole 10 and the second hole 13 are blind holes. The first and second springs 11 and 14 are received through the first and second holes 10 and 13, thereby facilitating installation of the seal ring 16.
As shown in fig. 7, the first holes 10 and the second holes 13 of the sealing ring 16 are arranged alternately. By staggering the first holes 10 and the second holes 13, a partial structure of the sealing ring single body 17 is avoided.
As shown in fig. 4, spring housings 12 are respectively sleeved on the sides of the first spring 11 far from the first hole 10 and the second spring 14 far from the second hole 13. In this embodiment, the first spring 11 is provided with a first spring housing 1201 on the side away from the first hole 10, and the second spring 14 is provided with a second spring housing 1202 on the side away from the second hole 13. The first spring 11 and the second spring 14 are respectively wrapped in the first spring sleeve 1201 and the second spring sleeve 1202, so that the influence of high-temperature and high-pressure gas in the annular channel on the performance of the springs can be reduced while the springs are prevented from being inclined, the failure of the springs is prevented, and the stability of the sealing structure is improved.
As shown in fig. 4, the open-side portion of the spring housing 12 fitted to the first spring 11 is located in the first hole 10, and the open-side portion of the spring housing 12 fitted to the second spring 14 is located in the second hole 13. In the present embodiment, the opening-side portion of the first spring housing 1201 is located in the first hole 10, and the opening-side portion of the second spring housing 1202 is located in the second hole 13. By extending the spring housing 12 into the first hole 10 or the second hole 13, the stability of the mounting structure of the spring housing 12 is improved.
As shown in fig. 5 and 6, a through hole is drilled at the bottom of the spring housing 12, and an opening is formed in the side surface of the spring housing 12 and is communicated with the through hole. The gas inside the spring housing is communicated with the gas outside the spring housing through the through holes and the openings, so that the pressing force of the spring on the sealing ring 16 is not influenced by the gas pressure in the spring housing. Furthermore, the provision of the opening can facilitate the installation of the spring sleeve 12 into the first bore 10 or the second bore 13.
As shown in fig. 7 and 8, the seal ring 16 is formed by combining a plurality of identical seal ring single bodies 17. In this way, the seal ring 16 can be easily attached and detached.
As shown in fig. 7, a first sealing protruding section 18 and a second sealing protruding section 19 are respectively processed at two ends of the single sealing ring 17, and the first sealing protruding section 18 and the second sealing protruding section 19 of the adjacent single sealing ring 17 are sequentially overlapped. As shown in fig. 5, the single sealing ring 17a is adjacent to the single sealing ring 17b, the first protruding section 18 of the first single sealing ring 17a overlaps the second protruding section 19 of the second single sealing ring 17b, and since the first single sealing ring 17a and the second single sealing ring 17b are both compressed in the mounting groove 15, and the exhaust diffuser is used, the sealing ring 16 is subjected to pressure in the axial direction, so that the first protruding section 18 is compressed in the second protruding section 19, thereby achieving radial sealing.
As shown in fig. 4, the sealing structure further includes a sealing groove 8 and a sealing ring 9, the cross section of the sealing groove 8 is a trapezoid with the groove bottom width smaller than the groove opening width, and the cross section of the sealing ring 9 is a trapezoid matched with the sealing groove 8. The installation and the cooperation of sealing washer 9 and seal groove 8 are convenient for through trapezoidal cross-section to make sealing washer 9 compress tightly on the side of seal groove 8, make sealing washer 9 also can realize compressing tightly and sealed on the side of seal groove 8, improve sealed effect.
As shown in fig. 4, the number of the seal grooves 8 is plural, and the seal grooves 8 are spaced apart from each other, and the number of the seal rings 9 is the same as the number of the seal grooves 8. Carry out multi-level sealed through setting up a plurality of seal grooves 8 and sealing washer 9, avoid simultaneously seal groove 8 and sealing washer 9 set up too intensively through setting up the interval to make the atress of the structure at seal groove 8 place more even, thereby improve sealing performance and seal structure reliability.
The above technical features constitute the best embodiment of the present invention, which has strong adaptability and best implementation effect, and unnecessary technical features can be added or subtracted according to actual needs to meet the needs of different situations.
Finally, it should be noted that the above-mentioned contents are only used for illustrating the technical solutions of the present invention, and not for limiting the protection scope of the present invention, and those skilled in the art can make various combinations, modifications or substitutions on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention.
Claims (10)
1. The utility model provides a gas turbine exhaust diffuser seal structure, includes anterior segment diffuser inner ring, back end diffuser inner ring, sealing ring, first spring, second spring, anterior segment diffuser inner ring with back end diffuser inner ring cooperatees, its characterized in that: the gas-gas burner is characterized in that one of the front-section diffuser inner ring and the rear-section diffuser inner ring is provided with a mounting groove, the mounting groove is formed in the matching surface of the front-section diffuser inner ring and the rear-section diffuser inner ring, the sealing ring is partially located in the mounting groove, the side face of the mounting groove is provided with the first spring, the first spring enables the sealing ring to eject gas in the direction of pressure generated by the sealing ring, the bottom of the mounting groove is provided with the second spring, and the second spring enables the sealing ring to eject out of the mounting groove.
2. The gas turbine exhaust diffuser seal arrangement of claim 1, wherein: and a first hole for accommodating the first spring and a second hole for accommodating the second spring are arranged on the sealing ring, and the first hole and the second hole are blind holes.
3. A gas turbine exhaust diffuser seal construction as set forth in claim 2 wherein: the first holes and the second holes on the sealing ring are arranged in a staggered mode.
4. A gas turbine exhaust diffuser seal construction as set forth in claim 2 wherein: one side of the first spring, which is far away from the first hole, and one side of the second spring, which is far away from the second hole, are respectively sleeved with a spring sleeve.
5. The gas turbine exhaust diffuser seal arrangement of claim 4, wherein: the part, sleeved on one side of the opening of the spring sleeve of the first spring, is positioned in the first hole, and the part, sleeved on one side of the opening of the spring sleeve of the second spring, is positioned in the second hole.
6. The gas turbine exhaust diffuser seal arrangement of claim 4, wherein: the spring sleeve is characterized in that a through hole is drilled at the bottom of the spring sleeve, an opening is formed in the side face of the spring sleeve, and the opening is communicated with the through hole.
7. The gas turbine exhaust diffuser seal arrangement of claim 1, wherein: the sealing ring is formed by combining a plurality of identical sealing ring monomers.
8. The gas turbine exhaust diffuser seal arrangement of claim 7, wherein: the free both ends of sealing ring have processed first sealed section of stretching out and the sealed section of stretching out of second respectively, and is adjacent the free sealing ring first sealed section of stretching out with the sealed section of stretching out of second is overlap joint in proper order.
9. The gas turbine exhaust diffuser seal arrangement of claim 1, wherein: the sealing structure further comprises a sealing groove and a sealing ring, the cross section of the sealing groove is trapezoidal, the width of the groove bottom is smaller than that of the groove opening, and the cross section of the sealing ring is trapezoidal matched with the sealing groove.
10. The gas turbine exhaust diffuser seal arrangement of claim 9, wherein: the number of seal grooves is a plurality of, leave the interval between the seal groove, the quantity of sealing washer with the number of seal groove is the same.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011588349.3A CN112761743B (en) | 2020-12-29 | 2020-12-29 | Gas turbine exhaust diffuser seal structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011588349.3A CN112761743B (en) | 2020-12-29 | 2020-12-29 | Gas turbine exhaust diffuser seal structure |
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| Publication Number | Publication Date |
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| CN112761743A CN112761743A (en) | 2021-05-07 |
| CN112761743B true CN112761743B (en) | 2022-08-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011588349.3A Active CN112761743B (en) | 2020-12-29 | 2020-12-29 | Gas turbine exhaust diffuser seal structure |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113669451A (en) * | 2021-08-31 | 2021-11-19 | 湖北三江航天红林探控有限公司 | Sealing structure and application thereof in high-temperature and high-pressure system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1427182A (en) * | 2001-12-17 | 2003-07-02 | 乐金电子(天津)电器有限公司 | Diffusor structure of vortex compressor |
| JP2006090273A (en) * | 2004-09-27 | 2006-04-06 | Mitsubishi Heavy Ind Ltd | Fluid machine equipped with fluid sealing mechanism |
| CN101372904A (en) * | 2007-08-23 | 2009-02-25 | 通用电气公司 | Method, system and apparatus for turbine diffuser sealing |
| CN106574516A (en) * | 2014-08-25 | 2017-04-19 | 三菱日立电力***株式会社 | Gas turbine exhaust member, and exhaust chamber maintenance method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE202004019366U1 (en) * | 2004-12-15 | 2006-04-20 | Nash_Elmo Industries Gmbh | Compressor, in particular side channel compressor |
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2020
- 2020-12-29 CN CN202011588349.3A patent/CN112761743B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1427182A (en) * | 2001-12-17 | 2003-07-02 | 乐金电子(天津)电器有限公司 | Diffusor structure of vortex compressor |
| JP2006090273A (en) * | 2004-09-27 | 2006-04-06 | Mitsubishi Heavy Ind Ltd | Fluid machine equipped with fluid sealing mechanism |
| CN101372904A (en) * | 2007-08-23 | 2009-02-25 | 通用电气公司 | Method, system and apparatus for turbine diffuser sealing |
| CN106574516A (en) * | 2014-08-25 | 2017-04-19 | 三菱日立电力***株式会社 | Gas turbine exhaust member, and exhaust chamber maintenance method |
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| CN112761743A (en) | 2021-05-07 |
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Address after: No. 1188, Dongxin Road, Hangzhou, Zhejiang, 310022 Patentee after: Hangzhou Steam Turbine Holding Co.,Ltd. Address before: No. 1188, Dongxin Road, Hangzhou, Zhejiang, 310022 Patentee before: HANGZHOU TURBINE POWER GROUP CO.,LTD. |
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