CN107420136A - Combustion gas turbine - Google Patents
Combustion gas turbine Download PDFInfo
- Publication number
- CN107420136A CN107420136A CN201710321787.5A CN201710321787A CN107420136A CN 107420136 A CN107420136 A CN 107420136A CN 201710321787 A CN201710321787 A CN 201710321787A CN 107420136 A CN107420136 A CN 107420136A
- Authority
- CN
- China
- Prior art keywords
- middleware
- stator carrier
- retaining element
- combustion gas
- gas turbine
- 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.)
- Granted
Links
Classifications
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
-
- 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
-
- 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
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/31—Retaining bolts or nuts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of combustion gas turbine, it is carried：Compressor, within the compressor compressible air；Burner with combustion chamber, compressed air can be fed to burner within the compressor, and can make fuel combustion in the case where heating air when compressed air be present in the burner；Turbine, the air being heated in turbine can be depressured；Wherein, heated air can be conveyed to turbine from the combustion chamber in of burner via middleware, middleware is fixed at the stator carrier of turbine using the end in downstream；Wherein, middleware has with the retaining element for having female screwed hole in the end in downstream；Wherein, the retaining element of middleware is stretched into the recess of stator carrier of turbine；Wherein, what stator carrier had a non-threaded passes through groove；Wherein, the retaining element of middleware is assemblied at stator carrier via with non-threaded by hole and through the holding element by groove and the fixing bolt of the screwed hole of retaining element by hole, stator carrier of holding element.
Description
Technical field
The present invention relates to a kind of combustion gas turbine.
Background technology
For those skilled in the art referred in this, combustion gas turbine, such as industrial gas turbines it is basic
Structure is substantially known.So that as important component, combustion gas turbine with compressor, it is at least one with
The burner and turbine of combustion chamber.Within the compressor, compressed air stream, wherein, compressed air stream can within the compressor
It is fed to one or each combustion chamber of combustion gas turbine.In one of combustion gas turbine or each combustion chamber, exist
Make fuel combustion in the case of compressed air, thus heat air.Heated air combustion chamber quilt from one or each
The turbine of combustion gas turbine is conveyed to, wherein, heated air is depressured in turbine.So, from being provided by turbine and
By the operating power that this combustion gas turbine is drawn in the difference of the power of compressor consumption.By at one of burner or each
Energy in combustion chamber, which introduces, produces the difference.
As has already been discussed, heated air can be fed to turbine from corresponding combustion chamber in, definitely
The corresponding middleware via also referred to as transition piece is said to convey in ground.So, if combustion gas turbine includes multiple combustion chambers,
Then air can be conveyed to turbine from each combustion chamber via corresponding middleware.Corresponding middleware utilizes the end in downstream
Portion is fixed at the stator carrier of turbine.Here, at least one fixing bolt is led in extending through in the radial direction for middleware
The corresponding hole of leaf carrier and the corresponding hole of middleware.
Middleware from corresponding combustion chamber to combustion gas turbine or mistake for the flowing guiding in the direction of the turbine from
Part is crossed, is subjected in operation from temperature, pressure and the extreme load of vibration.As a result, middleware or transition piece have mostly
There is the shorter service life of the service life of the remainder than combustion gas turbine.Therefore need to replace middleware or transition piece.
From known combustion gas turbine in practice, this has resulted in difficulty, that is to say, that so so that middleware or transition piece are not
It can be changed in the case of a large amount of assembly works of remainder progress not to combustion gas turbine.
The content of the invention
Therefore the demand to such combustion gas turbine be present, i.e. wherein, assembling consumption replacement that can be lower is used for
The middleware or transition piece of flowing guiding of the heated air from corresponding combustion chamber to turbine direction.
Based on this, the object of the present invention is to realize new combustion gas turbine.The purpose passes through according to claim 1
Combustion gas turbine realize.According to the present invention, corresponding middleware has at least one with least one in the end in downstream
The retaining element in the individual female hole of tool.The corresponding retaining element of corresponding middleware stretches into the phase of the stator carrier of turbine
In the recess answered, wherein, stator carrier have at least one non-threaded by groove, it is in the section towards corresponding middleware
Place is configured to axially open.The corresponding retaining element of corresponding middleware passes through hole via with least one non-threaded
With it is at least one through holding element it is corresponding by hole, stator carrier it is corresponding by groove and corresponding retaining element
The corresponding holding element of the fixing bolt of corresponding screwed hole is assemblied at stator carrier.
The embodiments above of combustion gas turbine, i.e. corresponding middleware is via corresponding retaining element and corresponding guarantor
Holding fixed at the stator carrier of turbine of element and one or each fixing bolt allows in the case of low assembly cost more
Corresponding middleware is changed, fixing bolt passes through hole, the phase of stator carrier through the corresponding non-threaded of corresponding holding element
The non-threaded answered passes through groove and the corresponding screwed hole of corresponding retaining element.
For example, by simply punishing the corresponding fixing bolt that breaks in the section stretched out relative to corresponding holding element, very
Corresponding holding element can be extremely removed when fixing bolt blocks and is removed in the axial direction at stator carrier corresponding fixed
Element.The replacing of middleware or transition piece can be realized in the case where not continuing to decompose combustion gas turbine.
Preferably, corresponding holding element is followed by corresponding fixed member in the axial direction of corresponding middleware or stator carrier
Part and stator carrier.This allows corresponding middleware being especially advantageously fixed at stator carrier.
According to the scheme that is advantageously improved, corresponding retaining element can hingedly act on accordingly around rotation axis tipping
At middleware, particularly at radially extending corresponding protuberance cam-type, in corresponding middleware of middleware.
Preferably, corresponding rotation axis tangentially extends with the circumference of corresponding middleware.Hereby it is achieved that corresponding middleware exists
Especially advantageous fixation at stator carrier.Here, corresponding swingable link of the retaining element at corresponding middleware
It is particularly advantageous.
According to the scheme that is advantageously improved, there is the combustion of the recess for the flame tube to be accommodated for being used for corresponding combustion chamber respectively
Burn room housing to be dimensioned such that so that can assemble corresponding middleware at turbine and by it from turbine via recess
Place's dismounting.Thus, corresponding middleware can be simply removed at combustion gas turbine in the axial direction, without carrying out gas turbine
The further decomposition of machine.
Brief description of the drawings
The preferable improvement project of the present invention is drawn by dependent claims and following description.Elaborate this with reference to the accompanying drawings
The embodiment of invention, and it is not only restricted to this.Wherein：
Fig. 1 show in cross section combustion gas turbine；
Fig. 2 shows the perspective view of the details of Fig. 1 combustion gas turbine；
Fig. 3 shows the details of the combustion gas turbine of Fig. 2 with the holding element pulled down；
Fig. 4 shows Fig. 3 top view；And
Fig. 5 shows the perspective view of another details of Fig. 1 combustion gas turbine.
List of numerals
10 combustion gas turbines
11 compressors
12 turbines
13 burners
14 housings
15 axles
16 housings
17 axles
18 burner shells
19 recesses
20 flame tubes
21 combustion chambers
22 diffusers
23 flow channels
24 middlewares
25 ends
26 stator carriers
27 retaining elements
28 screwed holes
29 recesses
30 pass through groove
31 holding elements
32 fixing bolts
33 parts
34 parts
35 rotation axis
36 protuberances
37 protuberances
38 sections
39 stators
40 flow into seamed edge
41 flow out seamed edge
42 closures.
Embodiment
The present invention relates to a kind of combustion gas turbine.Fig. 1 shows in compressor 11, turbine 12 and has at least one burning
The axial cross section of combustion gas turbine 10 is passed through in room, the region of burner 13 that is connected between compressor 11 and turbine 12.
The housing 14 of the stator side with multiple compressor stages and the axle 15 of rotor-side are shown in compressor 11.Show in turbine 12
The housing 16 of stator side and the axle 17 of rotor-side with multiple stage of turbines are shown.The axle 15 and turbine of the rotor-side of compressor 11
The axle 17 of 12 rotor-side interconnects.
Burner shell 18 is shown in burner 13, it is connected to the housing 14 of the stator side of compressor 11 and turbine
Between the housing 16 of 12 stator side.Preferably, burner shell 18 has multiple recesses 19, wherein, receiving portion it is each recessed
Mouth 19 is respectively used to accommodate at least one flame tube 20 of corresponding combustion chamber 21.On the periphery of burner shell 18, it is used for
The recess 19 of receiving flame tube 20 is preferably observed in the circumferential evenly distributedly to be arranged.
Compressor 11 is used for compressed air stream.Compressed air flow through by diffuser 22 leave compressor 11 and via
Diffuser 22 is reached in the flow cavity 23 of annular, and flow cavity 23 is provided by burner shell 18.
From the flow channel 23s of the ring type of burner shell 18, compressed air reaches each combustion chamber 21
In the region for reaching in region and thus each flame tube 20, wherein, fire fuel in the region of corresponding combustion chamber 21
Burn and heat air herein.
Heated air is fed to turbine 12 from corresponding combustion chamber 21s, wherein, middleware 24 is used to convey.
From each combustion chamber 21s, heated air can be fed to the turbine of combustion gas turbine 10 via middleware 24 respectively
12。
Fig. 2 and 3 shows the detailed view of the perspective of middleware 24, and heated air can be via the middleware 24 from combustion
Room 21 is burnt to set out and is fed to turbine 12, wherein, the middleware 24 shown in figs 2 and 3 is at the end 25 in downstream and turbine
12 stator carrier 26 is connected.It is in this that the present invention relates to this middleware 24 and the connecting portion of the stator carrier 26 of turbine 12
Details.
The middleware 24 shown in figs 2 and 3 is fixed using end 25 downstream via at least one retaining element 27
At the stator carrier 26 of turbine 12, wherein, corresponding retaining element 27 has the female hole 28 of at least one band.From figure
It can be learnt in 4, two are constructed at shown retaining element 27 with female such screwed hole 28.
The stator that the corresponding retaining element 27 of the middleware 24 shown in figs 2 and 3 stretches into turbine 12 in the axial direction carries
In the corresponding recess 29 of body 26, wherein, corresponding recess 29 opens wide and towards corresponding middleware 24 in the axial direction.Stator
Carrier 26 have at least one non-threaded by groove 30, it is configured to axially open at the section towards middleware 24.Can
Learnt from Fig. 4, for corresponding retaining element 27 constructed at stator carrier 26 two such non-threadeds
Axle upwardly extend by groove 30.
In order to which the middleware shown in figs 2 and 3 24 is fixed at stator carrier 26, there is at least one non-threaded
Pass through the corresponding holding element 31 and corresponding retaining element 27 and the collective effect of stator carrier 26 in hole.Corresponding holding element
31 non-threaded by each in hole be used for accommodate and guide corresponding fixing bolt 32.Corresponding fixing bolt 32
Pass through the and of groove 30 through the corresponding non-threaded by hole, stator carrier 26 of the corresponding non-threaded of holding element 31 herein
The corresponding screwed hole 28 of retaining element 26.It can be learnt from Fig. 2, corresponding holding element 31 observes section in the axial direction
Ground is followed by or surrounded corresponding retaining element 27 and stator carrier 36.
Corresponding fixation of the middleware 24 at the stator carrier 26 of turbine 12 is accordingly by least one retaining element
27 and the collective effect of corresponding holding element 31 and at least one fixing bolt 32 realize.One or each fixing bolt 32 exist
This produces the power between corresponding retaining element 27 and stator carrier 26, thus produces the connection of power cooperation.In addition, fixed spiral shell
Bolt 31 and corresponding holding element 31 via form fit the corresponding retaining element 27 that is connected.
The corresponding corresponding screwed hole 28 of retaining element 27, the corresponding of stator carrier 26 are by groove 30 and accordingly
Diametrically being observed by hole for the corresponding non-threaded of holding element 31 is aligned with each other, wherein, corresponding retaining element 27 exists
Observation is centrally positioned between the inner radial section of part 24 and the holding element 31 of radially outer in the radial direction.
In shown preferred embodiment, stator carrier 26 implements into split, wherein, stator carrier have towards
The Part I 34 and the Part II 33 back to corresponding middleware 24 of corresponding middleware 24.Here, stator carrier 26
Recess 29 is constructed at the part 34 towards middleware 24 of stator carrier 26.Equally, being constructed by groove 30 for non-threaded is being led
At the part 34 of leaf carrier 26.
In the shown preferred embodiment of the present invention, corresponding retaining element 27 can around the tipping of rotation axis 35
Hingedly act at middleware 24, wherein, the rotation axis 35 tangentially extends relative to the circumference of corresponding middleware 24.
It is prominent that corresponding retaining element 27 acts on diametrically extending for the cam-type of middleware 24 via corresponding rotation axis 35
Go out at portion 36, wherein, the protuberance 36 is abutted in using axial face at the axial face of stator carrier 26.
Corresponding retaining element 27 stretches into the corresponding recess 29 of stator carrier 26 section in the axial direction, wherein, lead to
The protuberance 37 for crossing the radially outer of retaining element 27 limits corresponding retaining element 27 into the recess 29 of stator carrier 26
Introducing depth.As can be preferably learnt from Fig. 2, corresponding holding element 31 is surrounded or is followed by side in the axial direction
The protuberance 37 of retaining element 27.
As preferably can learnt from Fig. 2 and 3, the composition of two parts 33 and 34 of stator carrier 26 is internally positioned
Groove, stator are threaded into the groove using corresponding section 38.Stator 39 forms guide vane ring, and it is used herein to heated air
Flowing guiding from from middleware 24 to the direction for the guide vane ring being connected at the guide vane ring of turbine 12.Stator 39, which has, to be flowed into
Seamed edge 40, flow out seamed edge 41 and what is extended between flowing into seamed edge 40 and flowing out seamed edge 41 draw for flowing
Lead on the pressure side and suction side.
In order to dismantle middleware 24, it is necessary to only unclamp one or each fixing bolt 32, or be stuck in fixing bolt
Make its disjunction during radially outwardly relative at the corresponding section for keeping section 31 to stretch out.Then then, phase can simply be dismantled
The holding element 31 answered.Afterwards, corresponding middleware 24 is and then removed at stator carrier 26 in the axial direction, definitely
Say, thus can by corresponding retaining element 27 if necessary with one or it is each it is also extending in retaining element 27, be broken
Fixing bolt 32 together in the axial direction from accordingly by groove 30 pull out and in the axial direction from stator carrier 26
Pulled out in recess 29.The stator carrier 26 of turbine 12 need not be taken.
In addition propose, be so designed that the recess 19 of burner shell 18, i.e. in can assembling and dismantle by recess 19
Between part 24, thus, the interior diameter of recess 19 is more than the overall diameter of middleware 24.So, thus can be simply via in combustion chamber
Recess 19 in housing 18 takes out the middleware 24 of closing and positions new middleware 24 and assembled in stator carrier
At 26.
The embodiments above of combustion gas turbine 10, i.e. corresponding middleware 24 is via corresponding retaining element 27 and phase
The holding element 31 answered and one or each fixation of the fixing bolt 32 at the stator carrier 26 of turbine 12, it is allowed in low dress
With corresponding middleware 24 is changed in the case of cost, fixing bolt 32 passes through the corresponding non-threaded of corresponding holding element 31
Pass through hole, the corresponding screwed hole 28 for passing through groove 30 and corresponding retaining element 27 of the corresponding non-threaded of stator carrier 26.
When even when one or each fixing bolt 32 should fail, also corresponding middleware 24 can be axially toward stator carrier 26
The direction of burner 13 pulled out from the stator carrier 26 of turbine 12 and the recess of respective design via burner shell 18
19 remove corresponding middleware 24, in the opposite direction to assemble new middleware 24 at stator carrier 26.Fixed spiral shell
Bolt 32 is engaged using retaining element 27 of its external screw thread only with corresponding middleware 24.In the region of stator carrier 26, Gu
Determine bolt 32 to pass through by groove 30 and in the region of corresponding holding element 31 only through axially open non-threaded
Non-threaded passes through hole.Fixing bolt 32 and holding element 31 can approach via the pilot hole of the closing of burner shell 18, Fig. 1
Show this closure of this pilot hole.
Claims (10)
1. a kind of combustion gas turbine (10), it is carried
Compressor (11), the compressible air in the compressor (11)；
At least one burner (13) with combustion chamber (21), compressed air stream can be defeated in the compressor (11)
The air is being heated when giving the burner (13), and compressed air be present in the burner (13)
In the case of can make fuel combustion；
Turbine (12), the air being heated described in the turbine (12) can be depressured；
Wherein, corresponding burning that can be via corresponding middleware (24) by the heated air from the burner (13)
Set out in room (21) and be conveyed to the turbine (12), the middleware (24) is fixed on the turbine using the end (25) in downstream
(12) stator carrier (26) place；Characterized in that,
Corresponding middleware (24) the end in the downstream (25) place with it is at least one with it is at least one have it is interior
The retaining element (27) of the screwed hole (28) of screw thread；
The corresponding retaining element (27) of corresponding middleware (24) stretches into the stator carrier (26) of the turbine (12)
In recess (29), wherein, the stator carrier (26) have at least one non-threaded by groove (30), it is towards the phase
It is configured at the section for the middleware (24) answered axially open；
The corresponding retaining element (27) of corresponding middleware (24) via with least one non-threaded by hole and
It is at least one that groove (30) and phase are passed through by hole, the corresponding of the stator carrier (26) through the corresponding of holding element (31)
Corresponding holding element (31) assembling of the fixing bolt (32) of the corresponding screwed hole (28) for the retaining element (27) answered
At stator carrier (26) place.
2. combustion gas turbine according to claim 1, it is characterised in that corresponding holding element (31) is in the phase
The axle for the middleware (24) answered, which looks up, is followed by corresponding retaining element (27) and the stator carrier (26).
3. combustion gas turbine according to claim 1 or 2, it is characterised in that corresponding retaining element (27) can be around
Hingedly act on corresponding middleware (24) place rotation axis (35) tipping.
4. combustion gas turbine according to claim 3, it is characterised in that corresponding rotation axis (36) and the phase
The circumference for the middleware (24) answered tangentially extends.
5. the combustion gas turbine according to claim 3 or 4, it is characterised in that corresponding retaining element (31) via
The rotation axis (35) acts on protuberance (36) place of the cam-type of corresponding middleware (24).
6. combustion gas turbine according to claim 5, it is characterised in that the protuberance (36) of the cam-type is in the phase
The middleware (24) answered radially extending and abutted in using axial face at the axial face of the stator carrier (26).
7. combustion gas turbine according to any one of claim 1 to 6, it is characterised in that corresponding retaining element
(27) corresponding screwed hole (28), the corresponding of the stator carrier (26) by groove (30) and corresponding keep member
Corresponding being radially aligned to by hole of part (31).
8. combustion gas turbine according to any one of claim 1 to 7, it is characterised in that the stator of the turbine (12)
Carrier (26) implement composition from, and it is included towards the part (34) of corresponding middleware (24) and back to the phase
The part (33) for the middleware (24) answered, wherein, one or each unlimited groove in the axial direction of the stator carrier (26)
(30) construction is at part (34) place towards corresponding middleware (24) of the stator carrier (26).
9. combustion gas turbine according to any one of claim 1 to 8, it is characterised in that burning chamber shell (18), it is
The flame tube (20) to be accommodated of corresponding combustion chamber (21) has the recess (19) for being so designed that size respectively so that warp
Corresponding middleware (24) can be assemblied in by the recess (19) by the turbine (12) and can be by it from the whirlpool
Take turns the dismounting of (12) place.
10. combustion gas turbine according to any one of claim 1 to 9, it is characterised in that corresponding middleware
(24) corresponding retaining element (27) be extended partially into the axial direction the stator carrier (26) of the turbine (12) in axial direction
It is upper opening wide and in the recess (29) towards corresponding middleware (24), wherein, corresponding retaining element (27)
Protuberance (37) limit in corresponding retaining element (27) to the recess (29) of the stator carrier (26) axially introduced into
Depth.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102016108461.1 | 2016-05-09 | ||
| DE102016108461.1A DE102016108461B4 (en) | 2016-05-09 | 2016-05-09 | gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107420136A true CN107420136A (en) | 2017-12-01 |
| CN107420136B CN107420136B (en) | 2021-02-26 |
Family
ID=60119115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710321787.5A Active CN107420136B (en) | 2016-05-09 | 2017-05-09 | Gas turbine |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JP6768564B2 (en) |
| KR (1) | KR102317807B1 (en) |
| CN (1) | CN107420136B (en) |
| CH (1) | CH712452B1 (en) |
| DE (1) | DE102016108461B4 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102020111200A1 (en) | 2020-04-24 | 2021-10-28 | Man Energy Solutions Se | Fastening device for the elastic suspension of a transition duct on a guide vane carrier of a gas turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101818659A (en) * | 2009-02-25 | 2010-09-01 | 通用电气公司 | Be used to keep the device of bucket cover plate |
| US20130200571A1 (en) * | 2010-03-24 | 2013-08-08 | Kawasaki Jukogyo Kabushiki Kaisha | Seal mechanism for use with turbine rotor |
| CN103573300A (en) * | 2012-07-30 | 2014-02-12 | 阿尔斯通技术有限公司 | Stationary gas turbine arrangement and method for performing maintenance work |
| US20160017730A1 (en) * | 2014-07-17 | 2016-01-21 | Siemens Energy, Inc. | Method and apparatus for attaching a transition duct to a turbine section in a gas turbine engine |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6662567B1 (en) * | 2002-08-14 | 2003-12-16 | Power Systems Mfg, Llc | Transition duct mounting system |
| US20060275107A1 (en) | 2005-06-07 | 2006-12-07 | Ioannis Alvanos | Combined blade attachment and disk lug fluid seal |
| US8322146B2 (en) * | 2007-12-10 | 2012-12-04 | Alstom Technology Ltd | Transition duct assembly |
| US8562000B2 (en) * | 2011-05-20 | 2013-10-22 | Siemens Energy, Inc. | Turbine combustion system transition piece side seals |
| US20130255276A1 (en) * | 2012-03-27 | 2013-10-03 | Alstom Technology Ltd. | Transition Duct Mounting System |
| US9702258B2 (en) * | 2014-07-01 | 2017-07-11 | Siemens Energy, Inc. | Adjustable transition support and method of using the same |
| US9359955B2 (en) * | 2014-08-28 | 2016-06-07 | Siemens Energy, Inc. | Apparatus and method incorporating a transition AFT support for a gas turbine engine |
-
2016
- 2016-05-09 DE DE102016108461.1A patent/DE102016108461B4/en active Active
-
2017
- 2017-02-10 CH CH00162/17A patent/CH712452B1/en unknown
- 2017-03-10 JP JP2017045849A patent/JP6768564B2/en active Active
- 2017-05-02 KR KR1020170056182A patent/KR102317807B1/en active IP Right Grant
- 2017-05-09 CN CN201710321787.5A patent/CN107420136B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101818659A (en) * | 2009-02-25 | 2010-09-01 | 通用电气公司 | Be used to keep the device of bucket cover plate |
| US20130200571A1 (en) * | 2010-03-24 | 2013-08-08 | Kawasaki Jukogyo Kabushiki Kaisha | Seal mechanism for use with turbine rotor |
| CN103573300A (en) * | 2012-07-30 | 2014-02-12 | 阿尔斯通技术有限公司 | Stationary gas turbine arrangement and method for performing maintenance work |
| US20160017730A1 (en) * | 2014-07-17 | 2016-01-21 | Siemens Energy, Inc. | Method and apparatus for attaching a transition duct to a turbine section in a gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CH712452B1 (en) | 2021-01-15 |
| KR20170126402A (en) | 2017-11-17 |
| DE102016108461A1 (en) | 2017-11-09 |
| KR102317807B1 (en) | 2021-10-25 |
| JP6768564B2 (en) | 2020-10-14 |
| CN107420136B (en) | 2021-02-26 |
| DE102016108461B4 (en) | 2022-12-01 |
| CH712452A2 (en) | 2017-11-15 |
| JP2017203618A (en) | 2017-11-16 |
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