CA2745120A1 - Flow machine - Google Patents
Flow machine Download PDFInfo
- Publication number
- CA2745120A1 CA2745120A1 CA2745120A CA2745120A CA2745120A1 CA 2745120 A1 CA2745120 A1 CA 2745120A1 CA 2745120 A CA2745120 A CA 2745120A CA 2745120 A CA2745120 A CA 2745120A CA 2745120 A1 CA2745120 A1 CA 2745120A1
- Authority
- CA
- Canada
- Prior art keywords
- structural component
- flow machine
- component part
- end portion
- bellows seal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Classifications
-
- 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
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
- F16J15/0887—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing the sealing effect being obtained by elastic deformation of the packing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/34—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
- F16J15/36—Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member connected by a diaphragm or bellow to the other member
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/50—Sealings between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall
- F16J15/52—Sealings between relatively-movable members, by means of a sealing without relatively-moving surfaces, e.g. fluid-tight sealings for transmitting motion through a wall by means of sealing bellows or diaphragms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J3/00—Diaphragms; Bellows; Bellows pistons
- F16J3/04—Bellows
- F16J3/047—Metallic bellows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Devices (AREA)
- Diaphragms And Bellows (AREA)
Abstract
A flow machine (1) has two structural component parts (10, 20) which cooperate with one another by a bellows seal (30) so that the bellows seal (30) forms a medium barrier between two spaces (40, 50) of the flow machine (1) which directly adjoin the two structural component parts (10, 20). According to the invention, the flow machine (1) is constructed as a gas turbine, and one space (40) of the two spaces (40, 50) is a hot-gas space of a high-pressure stage of the gas turbine.
Description
FLOW MACHINE
Field of the Invention The invention is directed to a flow machine.
Background of the Art A flow machine of the type mentioned above is known, e.g., from DE 1 751 075 Al.
In the flow machine which is described in this document and which is constructed as a pressure exchanger, two structural component parts cooperate with one another by means of a bellows seal so that the bellows seal forms a medium barrier between two spaces in the flow machine which adjoin the two structural component parts.
Summary It is the object of the invention to provide a novel solution for the use of a bellows seal in a flow machine.
This object is met by a flow machine (1) with two structural component parts (10, 20) which cooperate with one another by a bellows seal (30) so that the bellows seal (30) forms a medium barrier between two spaces (40, 50) of the flow machine (1) which directly adjoin the two structural component parts (10, 20), characterized in that the flow machine (1) is constructed as a gas turbine, wherein one space (40) of the two spaces (40, 50) is a hot-gas space of a high-pressure stage of the gas turbine.
According to the invention, a flow machine has two structural component parts which cooperate with one another by a bellows seal so that the bellows seal forms a medium barrier between two spaces of the flow machine which directly adjoin the two structural component parts. The flow machine according to the invention is characterized in that the flow machine is constructed as a gas turbine, wherein one of the two spaces is a hot-gas space of a high-pressure stage of the gas turbine.
It was recognized by the inventors that the sealing area directly at the hot-gas space of a high-pressure stage of a gas turbine is extremely vulnerable to leakage because a levelness of sealing surfaces cannot be ensured during operation of the gas turbine due to an irregular circumferential distribution in the main gas flow. Further, once a leak has occurred, it has an exacerbating effect on the unevenness of the sealing surfaces so that the leakage effect increases. Further, there is the risk of overheating of sealing elements and, as a result, the loss of preloading or sealing force of the sealing elements.
Leakage can be reliably prevented through the use, according to the invention, of a bellows seal in this area.
According to an embodiment form of the invention, the other space of the two spaces is constructed as a cooling air space of the high-pressure stage of the gas turbine.
According to another embodiment form of the invention, the bellows seal has a first end portion by which it seals against a first structural component part of the two structural component parts and a second end portion by which it seals against a second structural component part of the two structural component parts, the first end portion being fastened to the first structural component part so that a deformation-tolerant connection is produced.
On the one hand, the inventive fastening of the bellows seal provides a reliable positional stability of the bellows seal and, on the other hand, permits a certain deformation of the connection of the bellows seal and first structural component part and, therefore, allows the bellows seal to be adapted to specific mechanical parameters while retaining a good sealing quality.
The first end portion is preferably welded, soldered, screwed, and/or cemented to the first structural component part.
According to yet another embodiment form of the invention, the second end portion seals against the second structural component part by area contact based only on axial preloading.
In this way, a connection is provided between the bellows seal and the second structural component part which tolerates movement but is nevertheless tight against media.
According to another embodiment form of the invention, the first end portion is constructed in the form of a flange which proceeds from an outer diameter of a fold part of the bellows seal and extends radially outward beyond the outer diameter of the fold part and rests on a radially extending sealing surface of the first structural component part, and the second end portion is constructed in the form of a flange which proceeds from the outer diameter of the fold part and extends radially inward in the opposite direction of the first end portion and rests on a radially extending sealing surface of the second structural component part.
Owing to this construction, the first end portion can be fixedly mounted at the first structural component part in a particularly simple and convenient manner. The second end portion lies inside the outer diameter of the fold and is therefore protected against damage.
According to another embodiment form of the invention, the first end portion has an axially extending connection portion which is connected to the fold part by a material bond so that an intermediate space is formed between the fold part and the sealing surface of the first structural component part.
The connection portion provides a lever arm so that the first end portion can deform to a certain extent in the area of the connection portion when the bellows seal is axially loaded and therefore provides deformation tolerance.
According to yet another embodiment form of the invention, a supporting surface or guide surface which extends axially in direction of the first structural component part adjoins the sealing surface of the second structural component part so that the supporting surface provides a radially inward support for the fold part.
Accordingly, a radial buckling of the fold part of the bellows seal and, therefore, impairment of preloading and of the sealing effect are prevented in a reliable manner when the bellows seal is pushed together axially. Further, the supporting surface provides an axial guide for the bellows seal.
According to yet another embodiment form of the invention, the sealing surface of the second structural component part, the supporting surface, and the sealing surface of the first structural component part extend in such a way that together they form a U-shaped circumferential receiving pocket for the fold part of the bellows seal.
In this way, the fold part of the bellows seal is received in such a way that it is protected even more reliably against damage and axial buckling.
According to another embodiment form of the invention, the first structural component part is formed by a stator blade carrier and/or a seal carrier of the high-pressure stage of the gas turbine.
Finally, a seal system according to the invention in the form of a bellows seal in the high-pressure stage of a gas turbine is used to compensate for large changes in the axial sealing gap, and the tightness of the two structural component parts from one space (hot-gas space) to the other space (cooling air space) is achieved through a defined preloading and delta p.
As an inventive solution, a deformation-tolerant connection of the two seal elements (bellows seal and stator blade carrier) is provided while retaining a good sealing quality. To this end, three possibilities are suggested: welding the bellows seal to the stator blade carrier, wherein the bellows geometry is designed in such a way that the structural component parts and the weld need only tolerate a minimum of stresses; soldering the bellows seal; and/or a screw/clamping connection between the bellows seal and stator blade carrier.
Brief Description of the Drawings The invention will be described in more detail in the following with reference to a preferred embodiment form and the accompanying drawing.
Fig. 1 shows a schematic sectional view through a portion of a flow machine according to an embodiment form of the invention.
Fig. I is a schematic sectional view through a portion of a flow machine 1 according to an embodiment form of the invention which is constructed as a gas turbine.
Detailed Description The flow machine 1 has a first structural component part 10 and a second structural component part 20 which cooperate with one another by means of a bellows seal 30 such that the bellows seal 30 forms a medium barrier between a hot-gas space 40 of a high-pressure stage (not shown separately) of the flow machine 1, which hot-gas space 40 directly adjoins the two structural component parts 10, 20, and a cooling air space 50 of the high-pressure stage of the flow machine 1, which cooling air space 50 directly adjoins the two structural component parts 10, 20.
The first structural component part 10 is formed by a stator blade carrier of the high-pressure stage of the flow machine 1. The second structural component part 20 is formed, e.g., by a housing part of the high-pressure stage of the flow machine 1.
Field of the Invention The invention is directed to a flow machine.
Background of the Art A flow machine of the type mentioned above is known, e.g., from DE 1 751 075 Al.
In the flow machine which is described in this document and which is constructed as a pressure exchanger, two structural component parts cooperate with one another by means of a bellows seal so that the bellows seal forms a medium barrier between two spaces in the flow machine which adjoin the two structural component parts.
Summary It is the object of the invention to provide a novel solution for the use of a bellows seal in a flow machine.
This object is met by a flow machine (1) with two structural component parts (10, 20) which cooperate with one another by a bellows seal (30) so that the bellows seal (30) forms a medium barrier between two spaces (40, 50) of the flow machine (1) which directly adjoin the two structural component parts (10, 20), characterized in that the flow machine (1) is constructed as a gas turbine, wherein one space (40) of the two spaces (40, 50) is a hot-gas space of a high-pressure stage of the gas turbine.
According to the invention, a flow machine has two structural component parts which cooperate with one another by a bellows seal so that the bellows seal forms a medium barrier between two spaces of the flow machine which directly adjoin the two structural component parts. The flow machine according to the invention is characterized in that the flow machine is constructed as a gas turbine, wherein one of the two spaces is a hot-gas space of a high-pressure stage of the gas turbine.
It was recognized by the inventors that the sealing area directly at the hot-gas space of a high-pressure stage of a gas turbine is extremely vulnerable to leakage because a levelness of sealing surfaces cannot be ensured during operation of the gas turbine due to an irregular circumferential distribution in the main gas flow. Further, once a leak has occurred, it has an exacerbating effect on the unevenness of the sealing surfaces so that the leakage effect increases. Further, there is the risk of overheating of sealing elements and, as a result, the loss of preloading or sealing force of the sealing elements.
Leakage can be reliably prevented through the use, according to the invention, of a bellows seal in this area.
According to an embodiment form of the invention, the other space of the two spaces is constructed as a cooling air space of the high-pressure stage of the gas turbine.
According to another embodiment form of the invention, the bellows seal has a first end portion by which it seals against a first structural component part of the two structural component parts and a second end portion by which it seals against a second structural component part of the two structural component parts, the first end portion being fastened to the first structural component part so that a deformation-tolerant connection is produced.
On the one hand, the inventive fastening of the bellows seal provides a reliable positional stability of the bellows seal and, on the other hand, permits a certain deformation of the connection of the bellows seal and first structural component part and, therefore, allows the bellows seal to be adapted to specific mechanical parameters while retaining a good sealing quality.
The first end portion is preferably welded, soldered, screwed, and/or cemented to the first structural component part.
According to yet another embodiment form of the invention, the second end portion seals against the second structural component part by area contact based only on axial preloading.
In this way, a connection is provided between the bellows seal and the second structural component part which tolerates movement but is nevertheless tight against media.
According to another embodiment form of the invention, the first end portion is constructed in the form of a flange which proceeds from an outer diameter of a fold part of the bellows seal and extends radially outward beyond the outer diameter of the fold part and rests on a radially extending sealing surface of the first structural component part, and the second end portion is constructed in the form of a flange which proceeds from the outer diameter of the fold part and extends radially inward in the opposite direction of the first end portion and rests on a radially extending sealing surface of the second structural component part.
Owing to this construction, the first end portion can be fixedly mounted at the first structural component part in a particularly simple and convenient manner. The second end portion lies inside the outer diameter of the fold and is therefore protected against damage.
According to another embodiment form of the invention, the first end portion has an axially extending connection portion which is connected to the fold part by a material bond so that an intermediate space is formed between the fold part and the sealing surface of the first structural component part.
The connection portion provides a lever arm so that the first end portion can deform to a certain extent in the area of the connection portion when the bellows seal is axially loaded and therefore provides deformation tolerance.
According to yet another embodiment form of the invention, a supporting surface or guide surface which extends axially in direction of the first structural component part adjoins the sealing surface of the second structural component part so that the supporting surface provides a radially inward support for the fold part.
Accordingly, a radial buckling of the fold part of the bellows seal and, therefore, impairment of preloading and of the sealing effect are prevented in a reliable manner when the bellows seal is pushed together axially. Further, the supporting surface provides an axial guide for the bellows seal.
According to yet another embodiment form of the invention, the sealing surface of the second structural component part, the supporting surface, and the sealing surface of the first structural component part extend in such a way that together they form a U-shaped circumferential receiving pocket for the fold part of the bellows seal.
In this way, the fold part of the bellows seal is received in such a way that it is protected even more reliably against damage and axial buckling.
According to another embodiment form of the invention, the first structural component part is formed by a stator blade carrier and/or a seal carrier of the high-pressure stage of the gas turbine.
Finally, a seal system according to the invention in the form of a bellows seal in the high-pressure stage of a gas turbine is used to compensate for large changes in the axial sealing gap, and the tightness of the two structural component parts from one space (hot-gas space) to the other space (cooling air space) is achieved through a defined preloading and delta p.
As an inventive solution, a deformation-tolerant connection of the two seal elements (bellows seal and stator blade carrier) is provided while retaining a good sealing quality. To this end, three possibilities are suggested: welding the bellows seal to the stator blade carrier, wherein the bellows geometry is designed in such a way that the structural component parts and the weld need only tolerate a minimum of stresses; soldering the bellows seal; and/or a screw/clamping connection between the bellows seal and stator blade carrier.
Brief Description of the Drawings The invention will be described in more detail in the following with reference to a preferred embodiment form and the accompanying drawing.
Fig. 1 shows a schematic sectional view through a portion of a flow machine according to an embodiment form of the invention.
Fig. I is a schematic sectional view through a portion of a flow machine 1 according to an embodiment form of the invention which is constructed as a gas turbine.
Detailed Description The flow machine 1 has a first structural component part 10 and a second structural component part 20 which cooperate with one another by means of a bellows seal 30 such that the bellows seal 30 forms a medium barrier between a hot-gas space 40 of a high-pressure stage (not shown separately) of the flow machine 1, which hot-gas space 40 directly adjoins the two structural component parts 10, 20, and a cooling air space 50 of the high-pressure stage of the flow machine 1, which cooling air space 50 directly adjoins the two structural component parts 10, 20.
The first structural component part 10 is formed by a stator blade carrier of the high-pressure stage of the flow machine 1. The second structural component part 20 is formed, e.g., by a housing part of the high-pressure stage of the flow machine 1.
The bellows seal 30 is preferably produced from a heat-resistant, flexible metal or plastic.
The bellows seal 30 has a first end portion 31 by which it seals against the first structural component part 10 and a second end portion 32 by which it seals against the second structural component part 20.
The first end portion 31 is fastened to the first structural component part 10 by welding, soldering, screwing, or clamping so that a deformation-tolerant connection is produced. In the present embodiment form, the first end portion 31 is welded on or soldered on, for example.
To this end, the first end portion 31 is constructed in the form of a flange which proceeds from an outer diameter 33a of a fold part 33 of the bellows seal 30 and extends radially outward beyond the outer diameter 33a of the fold part 33 and rests on a radially extending sealing surface 11 of the first structural component part 10.
Further, the first end portion 31 has an axially extending connection portion 31 a which is joined to the fold part 33 by a material bond or is formed integral with the fold part 33 so that an intermediate space RI is formed between the fold part 33 and the sealing surface 11 of the first structural component part 10.
When the bellows seal 30 is pushed together axially, the fold part 33 can deform into the intermediate space R1 by means of a deformation of the connection portion 31 a acting as a lever arm so that the connection provides deformation tolerance between the first end portion 31 and the first structural component part 10.
The second end portion 32 seals against the second structural component part 20 by area contact that is based solely on axial preloading in the direction of the second structural component part 20.
For this purpose, the second end portion 32 is constructed in the form of a flange which proceeds from the outer diameter 33a of the fold part 33 and extends radially inward in the opposite direction of the first end portion 31 and rests on a radially extending sealing surface 21 of the second structural component part 20.
A supporting surface 22 which extends axially in direction of the first structural component part 10 adjoins the sealing surface 21 of the second structural component part 20 so that the supporting surface 22 provides a radially inward support for the fold part 33.
The bellows seal 30 has a first end portion 31 by which it seals against the first structural component part 10 and a second end portion 32 by which it seals against the second structural component part 20.
The first end portion 31 is fastened to the first structural component part 10 by welding, soldering, screwing, or clamping so that a deformation-tolerant connection is produced. In the present embodiment form, the first end portion 31 is welded on or soldered on, for example.
To this end, the first end portion 31 is constructed in the form of a flange which proceeds from an outer diameter 33a of a fold part 33 of the bellows seal 30 and extends radially outward beyond the outer diameter 33a of the fold part 33 and rests on a radially extending sealing surface 11 of the first structural component part 10.
Further, the first end portion 31 has an axially extending connection portion 31 a which is joined to the fold part 33 by a material bond or is formed integral with the fold part 33 so that an intermediate space RI is formed between the fold part 33 and the sealing surface 11 of the first structural component part 10.
When the bellows seal 30 is pushed together axially, the fold part 33 can deform into the intermediate space R1 by means of a deformation of the connection portion 31 a acting as a lever arm so that the connection provides deformation tolerance between the first end portion 31 and the first structural component part 10.
The second end portion 32 seals against the second structural component part 20 by area contact that is based solely on axial preloading in the direction of the second structural component part 20.
For this purpose, the second end portion 32 is constructed in the form of a flange which proceeds from the outer diameter 33a of the fold part 33 and extends radially inward in the opposite direction of the first end portion 31 and rests on a radially extending sealing surface 21 of the second structural component part 20.
A supporting surface 22 which extends axially in direction of the first structural component part 10 adjoins the sealing surface 21 of the second structural component part 20 so that the supporting surface 22 provides a radially inward support for the fold part 33.
As can be seen from Fig. 1, the sealing surface 21 and the supporting surface 22 of the second structural component part 20 and the sealing surface 11 of the first structural component part extend in such a way that together they form a U-shaped circumferential receiving pocket for the fold part 33 of the bellows seal 30 so that the fold part 33 is reliably protected against damage and axial buckling and is guided axially.
Claims (10)
1. A flow machine (1) with two structural component parts (10, 20) which cooperate with one another by a bellows seal (30) so that the bellows seal (30) forms a medium barrier between two spaces (40, 50) of the flow machine (1) which directly adjoin the two structural component parts (10, 20), characterized in that the flow machine (1) is constructed as a gas turbine, wherein one space (40) of the two spaces (40, 50) is a hot-gas space of a high-pressure stage of the gas turbine.
2. The flow machine (1) according to claim 1, wherein the other space (50) of the two spaces (40, 50) is constructed as a cooling air space of the high-pressure stage of the gas turbine.
3. The flow machine (1) according to claim 1 or 2, wherein the bellows seal (30) has a first end portion (31) by which it seals against a first structural component part (10) of the two structural component parts (10, 20) and a second end portion (32) by which it seals against a second structural component part (20) of the two structural component parts (10, 20), and wherein the first end portion (31) is fastened to the first structural component part (10) so that a deformation-tolerant connection is produced.
4. The flow machine (1) according to claim 3, wherein the second end portion (32) seals against the second structural component part (20) by area contact that is based only on axial preloading.
5. The flow machine (1) according to claim 3 or 4, wherein the first end portion (31) is one of welded, soldered, screwed, and cemented to the first structural component part (10).
6. The flow machine (1) according to any one of claims 3 to 5, wherein the first end portion (31) is constructed in as a flange which proceeds from an outer diameter (33a) of a fold part (33) of the bellows seal (30) and extends radially outward beyond the outer diameter (33a) of the fold part (33) and rests on a radially extending sealing surface (11) of the first structural component part (10), and wherein the second end portion (32) is constructed in as a flange which proceeds from the outer diameter (33a) of the fold part (33) and extends radially inward in an opposite direction of the first end portion (31) and rests on a radially extending sealing surface (21) of the second structural component part (20).
7. The flow machine (1) according to claim 6, wherein the first end portion (31) has an axially extending connection portion (31a) which is connected to the fold part (33) by a material bond so that an intermediate space (R1) is formed between the fold part (33) and the sealing surface (11) of the first structural component part (10).
8. The flow machine (1) according to claim 6 or 7, wherein a supporting surface (22) which extends axially in direction of the first structural component part (10) adjoins the sealing surface (21) of the second structural component part (20) so that the supporting surface (22) provides a radially inward support for the fold part (33).
9. The flow machine (1) according to claim 8, wherein the sealing surface (21) of the second structural component part (20), the supporting surface (22), and the sealing surface (11) of the first structural component part (10) extend in such a way that together they form a receiving pocket for the fold part (33) of the bellows seal (30).
10. The flow machine (1) according to any one of claims 3 to 9, wherein the first structural component part (10) is formed by at least one of a stator blade carrier and a seal carrier of the high-pressure stage of the gas turbine.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102010031124.3 | 2010-07-08 | ||
| DE102010031124A DE102010031124A1 (en) | 2010-07-08 | 2010-07-08 | flow machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2745120A1 true CA2745120A1 (en) | 2012-01-08 |
Family
ID=44802574
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2745120A Abandoned CA2745120A1 (en) | 2010-07-08 | 2011-06-30 | Flow machine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20120321450A1 (en) |
| EP (1) | EP2405102A1 (en) |
| JP (1) | JP2012017847A (en) |
| CA (1) | CA2745120A1 (en) |
| DE (1) | DE102010031124A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102954210A (en) * | 2012-11-27 | 2013-03-06 | 中国北车集团大连机车研究所有限公司 | Turbocharger gas sealing structure |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9631517B2 (en) | 2012-12-29 | 2017-04-25 | United Technologies Corporation | Multi-piece fairing for monolithic turbine exhaust case |
| FR3016391B1 (en) * | 2014-01-10 | 2017-12-29 | Snecma | DEVICE FOR SEALING AND THERMALLY PROTECTING A TURBOMACHINE |
| US10087939B2 (en) * | 2015-07-21 | 2018-10-02 | Garrett Transportation I Inc. | Turbocharger systems with direct turbine interfaces |
| US10087821B2 (en) * | 2015-07-21 | 2018-10-02 | Garrett Transportation I Inc. | Turbocharger systems with direct turbine interfaces |
| US11473437B2 (en) * | 2015-09-24 | 2022-10-18 | General Electric Company | Turbine snap in spring seal |
| WO2017103960A1 (en) * | 2015-12-17 | 2017-06-22 | 三菱重工コンプレッサ株式会社 | Gas seal structure and centrifugal compressor |
| KR102038112B1 (en) * | 2017-10-13 | 2019-10-29 | 두산중공업 주식회사 | Combustor and gas turbine including the same |
| US11396947B2 (en) * | 2019-12-05 | 2022-07-26 | Eaton Intelligent Power Limited | Face seal with welded bellows |
| US11655721B2 (en) | 2020-10-29 | 2023-05-23 | Borgwarner Inc. | Turbocharger including a sealing assembly |
Family Cites Families (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB579775A (en) * | 1943-10-23 | 1946-08-15 | Armstrong Siddeley Motors Ltd | Improvements relating to labyrinth packings for elastic fluid turbines |
| FR962918A (en) * | 1947-03-11 | 1950-06-23 | ||
| US3332610A (en) * | 1965-09-08 | 1967-07-25 | Welch Scient Company | Shaft seal with cooling means |
| GB1181813A (en) | 1967-03-30 | 1970-02-18 | Rolls Royce | Improvements in or relating to Pressure Exchangers |
| DE1942346A1 (en) * | 1969-08-20 | 1971-03-04 | Motoren Turbinen Union | Device for sealing the rotor with respect to the stator in a turbine belonging to a gas turbine engine |
| US4030288A (en) * | 1975-11-10 | 1977-06-21 | Caterpillar Tractor Co. | Modular gas turbine engine assembly |
| US4573866A (en) * | 1983-05-02 | 1986-03-04 | United Technologies Corporation | Sealed shroud for rotating body |
| DE3830762C2 (en) * | 1988-09-09 | 1994-08-18 | Mtu Muenchen Gmbh | Device for holding a jacket ring in gas turbines |
| FR2646221B1 (en) * | 1989-04-19 | 1991-06-14 | Snecma | SEAL, DEVICE COMPRISING SAME AND APPLICATION TO A TURBOMACHINE |
| US6311983B1 (en) * | 1989-09-26 | 2001-11-06 | The Boeing Company | Combination static lift-off face contact seal and floating ring shaft seal |
| US5738490A (en) * | 1996-05-20 | 1998-04-14 | Pratt & Whitney Canada, Inc. | Gas turbine engine shroud seals |
| GB9717857D0 (en) * | 1997-08-23 | 1997-10-29 | Rolls Royce Plc | Fluid Seal |
| CN1165698C (en) * | 1998-07-15 | 2004-09-08 | 西门子公司 | Sealing system, esp for rotary machine |
| EP1130219A1 (en) * | 2000-03-02 | 2001-09-05 | Siemens Aktiengesellschaft | Turbine engine with sealing means between panels |
| JP2002013401A (en) * | 2000-06-29 | 2002-01-18 | Yanmar Diesel Engine Co Ltd | Exhauster of gas turbine |
| WO2002027148A1 (en) * | 2000-09-28 | 2002-04-04 | Siemens Westinghouse Power Corporation | Flexible interlocking combustor transition seal |
| US7334799B2 (en) * | 2002-12-23 | 2008-02-26 | Caterpillar Inc. | Sealing device for a turbocharger |
| US7178340B2 (en) * | 2003-09-24 | 2007-02-20 | Power Systems Mfg., Llc | Transition duct honeycomb seal |
| US6942445B2 (en) * | 2003-12-04 | 2005-09-13 | Honeywell International Inc. | Gas turbine cooled shroud assembly with hot gas ingestion suppression |
| EP1743087A1 (en) * | 2004-05-03 | 2007-01-17 | Honeywell International Inc. | Exhaust gas turbocharger with adjustable slide ring |
| US7784264B2 (en) * | 2006-08-03 | 2010-08-31 | Siemens Energy, Inc. | Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine |
| JP2009203841A (en) * | 2008-02-27 | 2009-09-10 | Hitachi Ltd | Gas turbine, sealing device of gas turbine and sealing method of gas turbine |
| US8016297B2 (en) * | 2008-03-27 | 2011-09-13 | United Technologies Corporation | Gas turbine engine seals and engines incorporating such seals |
| FR2937098B1 (en) * | 2008-10-15 | 2015-11-20 | Snecma | SEALING BETWEEN A COMBUSTION CHAMBER AND A TURBINE DISPENSER IN A TURBOMACHINE |
| JP5578903B2 (en) * | 2010-03-25 | 2014-08-27 | 三菱重工業株式会社 | Seal mechanism and steam turbine |
-
2010
- 2010-07-08 DE DE102010031124A patent/DE102010031124A1/en not_active Withdrawn
-
2011
- 2011-04-07 EP EP11161416A patent/EP2405102A1/en not_active Withdrawn
- 2011-06-27 JP JP2011141590A patent/JP2012017847A/en active Pending
- 2011-06-30 CA CA2745120A patent/CA2745120A1/en not_active Abandoned
- 2011-07-08 US US13/179,351 patent/US20120321450A1/en not_active Abandoned
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102954210A (en) * | 2012-11-27 | 2013-03-06 | 中国北车集团大连机车研究所有限公司 | Turbocharger gas sealing structure |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2405102A1 (en) | 2012-01-11 |
| DE102010031124A1 (en) | 2012-01-12 |
| JP2012017847A (en) | 2012-01-26 |
| US20120321450A1 (en) | 2012-12-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20120321450A1 (en) | Flow Machine | |
| US9447698B2 (en) | Double-walled turbocharger housing, flange and connection thereof | |
| US9876411B2 (en) | Cooling jacket comprising a sealing means | |
| KR101195543B1 (en) | Turbomachine and rotor-shaft seal | |
| US20110241341A1 (en) | Exhaust pipe for a motor vehicle and exhaust system | |
| WO2012081491A1 (en) | Seal structure for turbocharger housing | |
| US8118551B2 (en) | Casing and fluid machine | |
| US10731492B2 (en) | Component joint | |
| US20150093302A1 (en) | Seal for an exhaust aftertreatment device in an internal combustion engine | |
| WO2016009803A1 (en) | Sealing device | |
| JP2015161400A (en) | joint unit | |
| US9255654B2 (en) | Hard lead egress adapter for an instrumentation component | |
| US20140028021A1 (en) | Assembly having a flange | |
| JP2015025460A (en) | Seal structure for turbocharger housing | |
| JP4882827B2 (en) | Piping joint structure | |
| JP2007285371A (en) | Piping joint | |
| US9841016B2 (en) | Cryogenic, self-aligning cartridge seal | |
| US20200096113A1 (en) | Mechanical sealing device | |
| JP6234839B2 (en) | Delivery pipe | |
| KR101257876B1 (en) | Floating Sealing Apparatus For a Gas Turbine | |
| WO2024157877A1 (en) | Sealing device | |
| JP4851101B2 (en) | gasket | |
| JP2007085260A (en) | High-pressure fuel piping sealing structure of diesel engine | |
| EP3329114A1 (en) | High pressure fuel pump | |
| JP2015124853A (en) | Leakage repairing device and method for installing leakage repairing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| FZDE | Discontinued |
Effective date: 20140702 |