GB2452932A - Turbine or turbomachine with axial shaft-mounted compressor and turbine blades - Google Patents
Turbine or turbomachine with axial shaft-mounted compressor and turbine blades Download PDFInfo
- Publication number
- GB2452932A GB2452932A GB0718246A GB0718246A GB2452932A GB 2452932 A GB2452932 A GB 2452932A GB 0718246 A GB0718246 A GB 0718246A GB 0718246 A GB0718246 A GB 0718246A GB 2452932 A GB2452932 A GB 2452932A
- Authority
- GB
- United Kingdom
- Prior art keywords
- load
- shoulder
- turbine
- stud
- discs
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- 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
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
Abstract
A gas turbine rotor 1 comprises an intermediate shaft 3 to respective ends of which are mounted compressor blade discs 7b and turbine blade discs 8b. A stud 10, eg a single rod of high strength nickel based alloy, extends along the axis for securing the discs 7b, 8b to the intermediate shaft 3. The ends of the stud 10 engage first and second external pre-load nuts 11, 12. An intermediate point of the stud 10 is provided with a radially extending shoulder 15 to engage a face 13b of the intermediate shaft 3 to allow retention of a pre-load applied by the compressor pre-load nut 11 during the first stage of assembly. Subsequent application of a second pre-load by the turbine pre-load nut 12 reduces the pressure between the shoulder 15 and face 13b and may create a gap of eg 1 mm therebetween to allow a coolant flow along the shaft. Where the coolant path is not required, a seal (20,fig.3) may be provided in a rebate in the shoulder 15. The stud 10 may have a vibration restraint 16.
Description
A turbine and a method of manufacture This invention relates particularly but not exclusively to turbines or turbomachines with axial shaft mounted compressor turbine and power turbine blades.
In turbines, a number of discs including radial extending blades are mounted on an axially extending intermediate shaft to form a rotor.
There are compressor blade sets of discs and turbine blade sets of discs. The respective sets of discs are retained by a turbine nut and a compressor nut respectively which are used to apply a preload to tension the arrangement to ensure that it is secure during operation of the turbine.
In current turbines, the rotor is held together by a pair of tension studs. The first stud engages an outer end of the shaft by means of a threaded bore in the shaft. The second stud engages in a threaded bore of the other end of the shaft.
A typical prior art arrangement is shown in prior art figure 1 which is longitudinal section along the axis of a bladed rotor of a gas turbine. It includes left to right looking at the figures collectively, an axially extending compressor stud, a compressor nut, an inlet shaft, a set of compressor discs, an intermediate shaft, a turbine stud, a set of turbine discs and a turbine nut. In figure Ia, a threaded compressor stud is rotated into threaded engagement into a threaded bore in an intermediate shaft and compressor discs are slid over the compressor stud. An inlet shaft is then mounted onto the compressor stud and a compressor pre-load nut threaded onto the compressor stud end. A hydraulic tool is applied to stretch the stud and the compressor nut tightened to engage the inlet shaft before the tool is removed. This retains the pre-load applied to the compressor stud.
Figure 1 b shows a turbine stud threaded into the end of the intermediate shaft and then the next stage is to assemble the turbine discs onto the turbine stud with a turbine nut being threaded onto the other end of the turbine stud as shown in figure Ic. The hydraulic tool is applied to stretch the stud and the nut tightened to retain the pre-Ioad when the tool is removed.
I (
It will be appreciated that this is a complicated arrangement which requires careful machining for adequate operation and a long service life. In particular, the thread in the bore of the intermediate shaft is difficult to manufacture due to its location in the middle of the shaft.
The fatigue life of the thread is a limiting factor to the pre-load that can be applied to the tension studs.
The present invention arose in an attempt to mitigate these drawbacks.
According to the invention there is provided a gas turbine comprising a rotor rotatably mounted in a body about an axis which rotor comprising an intermediate shaft to one end of which are mounted a first set of discs and to a second end of which are mounted a second set of discs and a stud extending along the axis for securing the discs to the intermediate shaft which stud comprising a first and second external ends adapted to engage a first and a second pre-load nut respectively wherein the stud is provided with a radially extending shoulder at a point intermediate the stud ends to engage a face of the intermediate shaft to allow retention of an applied first pre-load by adjustment of the first pre-load nut.
Preferably, the shoulder is located relative to the face such that application of a second pre-load applied by, for example, an external tensioner acts to separate the shoulder from the face. The pre-load is retained via the second pre-load nut.
For some applications, the application of a pre-load will create a gap which may permit a fluid or gas flow to facilitate for example cooling or lubrication. Where this is not required a seal arrangement may be provided. The preferred form of seal is a metal "C"-ring seal held in a circumferential rebate in the shoulder to sealingly engage an inner bore of the intermediate shaft.
In alternative embodiments of the invention, it may be desirable to maintain the contact and for the first and second pre-load to differ.
In the described embodiment the first set of discs comprise compressor discs and the second set of discs comprise turbine discs.
The invention also provides a method for assembling a rotor for a turbine.
A specific embodiment of the invention will now be described, by way of example only, with reference to the drawings in which:
Figure 1 is a prior art figure;
Figure 2 shows a first embodiment of the invention during assembly; and Figure 3 shows an alternative embodiment.
As is shown in figure 2a, a rotor I is rotatably mounted in a cavity of body 2 of a gas turbine. It comprises blade discs mounted to an intermediate shaft. The cavity 2 in conjunction with stator blades (not shown) provides a fluid flow path to impinge on blades of the rotor 1. The rotor I has three main parts: an intermediate shaft, a compressor part and a turbine part. The intermediate shaft 3 is located between the compressor part 4 and the turbine part 5. The compressor part 4 also includes an inlet shaft 6.
The compressor part 4 comprises a first set of compressor blades 7a removeably located in blade discs 7b. The blades 7a are retained in the discs 7b by means of a slot formed in the disc which accepts a radial inner end of the blade which has a matching dovetail formation.
The blade discs 7b are fixed together by a clamping action of a stud acting on the inlet shaft 6 and the intermediate shaft 3 in a manner to be described later.
The turbine part is similarly formed of a second set of blades 8a held in discs 8b using a fir tree formation and clamped to the intermediate shaft 3 by the stud 10 in a manner to be described later.
The axial stud 10 is provided to hold the rotor together. First and second pre-load nuts 11 and 12 are provided at respective ends of the stud 10 and serve, when tightened against the inlet shaft 6 and an outer face of a turbine disc 9 following application of a hydraulic tool to stretch the stud 10, to pre-load the arrangement. Both nuts are provided with conical faces to engage conical surfaces peripheral to ends of an axial extending bore 13 to assist in centring the arrangement with the axis 14 of the rotor 1. At a position between the ends, the stud 10 extends radially outwards to provide a disc-like shoulder 15. This has a first bore riding part of generally cylindrical configuration 15a, a conical front abutment face 15b reducing over a length 15c from the radial dimension of the bore riding part 15a to the general radial dimension of the rest of the stud. The rear face 15 d is substantially normal to the axis 14.
Located at a point between the shoulder and the first stud end is a vibration restraint 16. This comprises two radially extending cylindrical machinings which close on the inner periphery defining the bore 13.
is The stud 10 is machined to provide the shoulder 15 and the vibration restraints 16 from a single rod of high strength nickel based alloy.
The bore 13 is configured, left to right as shown in the figure, to provide a substantially constant internal diameter portion over region labelled 17, then a radially narrow portion over region labelled 18 and then it broadens radially outwards over portion 19. The diameter of the bore over region 19 is greater than that over the region 18 but less than that over the region 17. The relative diameters of the bore 14 are determined by the stress concentrations in the compressor discs, the turbine discs and the intermediate shaft and in alternative embodiments of the invention could differ to that described.
Adjacent the conical surface I 5b of the shoulder 15 is an abutment face 13 b provided by the bore defining surface. This has an incline relative to the axis which matches that of the conical surface I 5b. In this assembled and pre-loaded state there is a gap therebetween of 1mm.
The way in which the rotor is assembled from its various component parts will now be described.
In a first set of steps as shown in figure 2b, the intermediate shaft 4 is slid along the stud from the left to the right until the abutment face 13b contacts the conical surface 15b, then the compressor discs, formed of blades 7a and discs 7b, and the inlet shaft 6 are slid along the stud again left to right. Pre-load nut 11 is then threaded onto the first end of the stud and tightened as is shown in figure 2c following application of a hydraulic tool to stretch the stud 10. The action of this is to clamp the arrangement together by virtue of pressure applied between the shoulder and the abutment face I 3b and the compressor nut 11 acting on the inlet shaft 7.
This completes the assembly of the compressor part of the rotor to the intermediate shaft 4.
The next stage in the assembly of the rotor is to slide the turbine discs over the right hand end of the stud 10. The turbine discs abut the right hand face of the intermediate shaft 4. The turbine pre- load nut 12 is then threaded onto the right-hand end of the stud 10 and a hydraulic tool applied to the stud 10 to stretch it. This firstly draws the turbine part into firm engagement to the intermediate shaft 4 and then, as the load is applied, the stud is stretched drawing the shoulder 15 out of contact with the abutment surface 13b. A gap of 1 mm results between these to arrive at the depicted assembled rotor shown in figure 2a. The turbine nut 12 is then tightened to retain the pre-load. This completes the assembly of the turbine part to the intermediate shaft and completes the rotor.
In this particular embodiment, the clearance between the shoulder 15 and the abutment surface I 3b permits the introduction of a coolant flow along the shaft to cool the stud 10 which for some applications is advantageous. (In figure 3, it will be seen that a seal 20 may be provided for other applications located in a circumferentially extending rebate in the shoulder 15. In this case the seal is a metal "C" ring seal.) In the described embodiment, the second pre-load is sufficient to draw the shoulder out of engagement with the abutment surface and to create a gap therebetween. However, the invention is equally applicable to merely reduce the surface pressure made therebetween without creating a gap. This will permit the first and second pre-loads to be different.
In order to ensure a good coolant flow grooves or channels may be formed in the surface 15b to facilitate flow along the shaft as it moves under the operating conditions.
In the described embodiments, the blades are held within slots in the discs by matching "fir tree" formations. In alternative arrangements, the blade and discs may be joined by welds or formed by machining both from a single piece of metal. In further alternative embodiments the blades may be clamped or "trapped" into position by adjacent discs or the blades could be held in axial slots or circumferential grooves. The blades could also be held by a mixture of these methods.
Claims (15)
- Claims 1. A gas turbine comprising a rotor rotatably mounted in a body about an axis which rotor comprising an intermediate shaft to one end of which are mounted a first set of discs and to a second end of which are mounted a second set of discs and a stud extending along the axis for securing the discs to the intermediate shaft which stud comprising a first and second external ends adapted to engage a first and a second pre-load nut respectively wherein the stud is provided with a radially extending shoulder at a point intermediate the stud ends to engage a face of the intermediate shaft to allow retention of an applied first pre-load by adjustment of the first pre-load nut.
- 2. A turbine as claimed in claim 1 wherein the shoulder is located relative to the face such that application of a second pre-load and its retention by the second preload nut acts to separate the shoulder from the face.
- 3. A turbine as claimed in claim 2 wherein the shoulder and face are relatively located such that application of the preload does not separate the shoulder from the face.
- 4. A turbine as claimed in claim 3 wherein the second pre-load is smaller than the first pre-load.
- 5. A turbine as claimed in claim 2 wherein a gap is in use present between the face and the shoulder.
- 6. A turbine as claimed in claim 5 wherein coolant flow is arranged along at least part of the stud through the gap between the shoulder and the face.
- 7. A turbine as claimed in claim 5 wherein a seal is provided on the shoulder to sealingly close the gap.
- 8. A turbine as claimed in any preceding claim wherein the first set of discs are a compressor discs and the second set of discs are turbine discs. (
- 9. A turbine as claimed in any preceding claim comprising one or several vibration restraints formed on the stud.
- 10. A turbine substantially as hereinbefore described with reference to and as illustrated by the drawings.
- 11. A method of assembling a turbine rotor comprising providing a stud with a shoulder, at least a first and a second set of blade discs, an intermediate shaft defining an axial bore; assembling the blade discs and in let shaft to the intermediate shaft; placing the inlet shaft and assembled blade discs over the stud with an abutment face of the periphery of the bore engaging the shoulder; assembling a first pie-load nut onto a first end of the stud, applying a preload to the end and the abutment via the shoulder to clamp the discs and shaft together and retaining the pie-load by application of the first pie-load nut.
- 12. A method as claimed in claim 11 comprising assembling the second discs to the other end of the stud and assembling a second pie- load nut to the other end, applying a second pre-load to an outer end of the stud to draw the shoulder and abutment surface in a direction out of engagement and applying the second pie-load nut to retain the second pie-load.
- 13. A method as claimed in claim 12 wherein the second pre-load creates a gap between the shoulder and abutment surface.
- 14. A method as claimed in claim 12 wherein the second pre-load is less than the first pre-load such that contact between the shoulder and the abutment surface is maintained.
- 15. A method of assembling a turbine rotor as hereinbefore described with reference to, and as illustrated by, the drawings.15. A method of assembling a turbine rotor as hereinbefore described with reference to, and as illustrated by, the drawings. -ItAmendments to the claims have been filed as follows: Claims 1. A gas turbine comprising a rotor rotatably mounted in a body about an axis which rotor comprising an intermediate shaft to one end of which are mounted a first set of discs and to a second end of which are mounted a second set of discs and a stud extending along the axis for securing the discs to the intermediate shaft which stud comprising a first and second external ends adapted to engage a first and a second pre-load nut respectively wherein the stud is provided with a radially extending shoulder at a point intermediate the stud ends to engage a face of the intermediate shaft to allow retention of an applied first pre-load by adjustment of the first pre-load nut.2. A turbine as claimed in claim I wherein the shoulder is located relative to the face such that application of a second pre-load and its retention by the second preload nut acts to separate the shoulder from the face.3. A turbine as claimed in claim 2 wherein the shoulder and face are relatively located such that application of the second preload does not separate the shoulder from the face.4. A turbine as claimed in claim 3 wherein the second pre-load is smaller than the first pre-load.5. A turbine as claimed in claim 2 wherein a gap is in use present between the face and the shoulder.6. A turbine as claimed in claim 5 wherein coolant flow is arranged along at least part of the stud through the gap between the shoulder and the face.7. A turbine as claimed in claim 5 wherein a seal is provided on the shoulder to sealingly close the gap.8. A turbine as claimed in any preceding claim wherein the first set of discs are a compressor discs and the second set of discs are turbine discs. to9. A turbine as claimed in any preceding claim comprising one or several vibration restraints formed on the stud.10. A turbine substantially as hereinbefore described with reference to and as illustrated by the drawings.11. A method of assembling a turbine rotor that comprises the constituent parts a stud with a shoulder, at least a first and a second set of blade discs, an intermediate shaft defining an axial bore, and an inlet shaft, the method comprising the steps of: assembling the first set of blade discs and the inlet shaft to the intermediate shaft by placing the intermediate shaft, the first set of blade discs, and the inlet shaft over the stud with an abutment face of the periphery of the bore of the intermediate shaft engaging the shoulder of the stud; assembling a first pre-load nut onto a first end of the stud, applying a preload to the first end and the abutment face via the shoulder to clamp the first set of discs and the inlet shaft together; and retaining the pre-load by application of the first pre-load nut.12. A method as claimed in claim 11 comprising assembling the second discs to the other end of the stud and assembling a second pre- load nut to the other end, applying a second pre-load to an outer end of the stud to draw the shoulder and abutment surface in a direction out of engagement and applying the second pre-load nut to retain the second pre-load.13. A method as claimed in claim 12 wherein the second pre-load creates a gap between the shoulder and abutment surface.14. A method as claimed in claim 12 wherein the second pre-load is less than the first pre-load such that contact between the shoulder and the abutment surface is maintained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0718246A GB2452932B8 (en) | 2007-09-19 | 2007-09-19 | A turbine and a method of manufacture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0718246A GB2452932B8 (en) | 2007-09-19 | 2007-09-19 | A turbine and a method of manufacture |
Publications (5)
| Publication Number | Publication Date |
|---|---|
| GB0718246D0 GB0718246D0 (en) | 2007-10-31 |
| GB2452932A true GB2452932A (en) | 2009-03-25 |
| GB2452932B GB2452932B (en) | 2009-08-05 |
| GB2452932A8 GB2452932A8 (en) | 2011-08-10 |
| GB2452932B8 GB2452932B8 (en) | 2011-08-10 |
Family
ID=38670139
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0718246A Expired - Fee Related GB2452932B8 (en) | 2007-09-19 | 2007-09-19 | A turbine and a method of manufacture |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2452932B8 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2415967A1 (en) * | 2010-08-03 | 2012-02-08 | Siemens Aktiengesellschaft | Gas turbine engine comprising a tension stud |
| CN102359396A (en) * | 2011-07-08 | 2012-02-22 | 西安交通大学 | Disc type rod fastening rotor structure with circumferential tension rod at turbine section for heavy gas turbine |
| EP2535514A2 (en) * | 2011-06-16 | 2012-12-19 | Thermodyn | Rotor structure including an internal hydraulic tension device |
| EP2880264A1 (en) * | 2012-09-07 | 2015-06-10 | Siemens Aktiengesellschaft | Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements |
| EP2927425A1 (en) * | 2014-03-31 | 2015-10-07 | Siemens Aktiengesellschaft | Rotor for a gas turbine having an anti-rotation device for a shaft nut |
| EP2933433A1 (en) * | 2014-04-15 | 2015-10-21 | Siemens Aktiengesellschaft | Method for assembling and/or disassembling a rotor section of a flow machine, corresponding mounting device and rotor disc |
| JP2016098809A (en) * | 2014-11-21 | 2016-05-30 | ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド | Gas turbine with plurality of tie rods and method of assembling the same |
| FR3039857A1 (en) * | 2015-08-04 | 2017-02-10 | Snecma | METHOD AND DEVICE FOR CLAMPING A ROTOR LINE OF TURBOMACHINE |
| EP2565381A3 (en) * | 2011-08-31 | 2017-03-08 | United Technologies Corporation | Assembly and method preventing tie shaft to unscrew |
| CN110238645A (en) * | 2019-05-31 | 2019-09-17 | 沈阳透平机械股份有限公司 | A kind of turbine rotor spindle mounted device and method |
| KR20210070711A (en) * | 2019-12-05 | 2021-06-15 | 두산중공업 주식회사 | Coupling structure for gas turbine and gas turbine comprising the same |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2672061A1 (en) | 2012-06-06 | 2013-12-11 | Siemens Aktiengesellschaft | Threaded shank, connection assembly and gas turbine engine for improved fatigue life of threads |
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|---|---|---|---|---|
| GB723882A (en) * | 1951-09-05 | 1955-02-16 | Vickers Electrical Co Ltd | Improvements in the construction of rotors for steam- and gas-turbines |
| GB898163A (en) * | 1960-01-21 | 1962-06-06 | Austin Motor Co Ltd | Improvements relating to gas turbines |
-
2007
- 2007-09-19 GB GB0718246A patent/GB2452932B8/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB723882A (en) * | 1951-09-05 | 1955-02-16 | Vickers Electrical Co Ltd | Improvements in the construction of rotors for steam- and gas-turbines |
| GB898163A (en) * | 1960-01-21 | 1962-06-06 | Austin Motor Co Ltd | Improvements relating to gas turbines |
Cited By (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9279327B2 (en) | 2010-08-03 | 2016-03-08 | Siemens Aktiengesellschaft | Gas turbine engine comprising a tension stud |
| WO2012016981A1 (en) | 2010-08-03 | 2012-02-09 | Siemens Aktiengesellschaft | Gas turbine engine comprising a tension stud |
| EP2415967A1 (en) * | 2010-08-03 | 2012-02-08 | Siemens Aktiengesellschaft | Gas turbine engine comprising a tension stud |
| RU2623354C2 (en) * | 2011-06-16 | 2017-06-23 | Термодин | Rotor containing internal hydraulic tensioning device and method of rotor assembly |
| CN102878112B (en) * | 2011-06-16 | 2017-11-28 | 热力学公司 | Include the rotor structure of internal hydraulic pressure tensioning apparatus |
| JP2013002448A (en) * | 2011-06-16 | 2013-01-07 | Thermodyn | Rotor structure including internal hydraulic tension device |
| CN102878112A (en) * | 2011-06-16 | 2013-01-16 | 热力学公司 | Rotor structure including an internal hydraulic tension device |
| EP2535514A3 (en) * | 2011-06-16 | 2014-08-06 | Thermodyn | Rotor structure including an internal hydraulic tension device |
| FR2976615A1 (en) * | 2011-06-16 | 2012-12-21 | Thermodyn | ROTOR STRUCTURE COMPRISING AN INTERNAL HYDRAULIC VOLTAGE DEVICE |
| US9631494B2 (en) | 2011-06-16 | 2017-04-25 | Thermodyn | Rotor structure including an internal hydraulic tension device |
| EP2535514A2 (en) * | 2011-06-16 | 2012-12-19 | Thermodyn | Rotor structure including an internal hydraulic tension device |
| CN102359396A (en) * | 2011-07-08 | 2012-02-22 | 西安交通大学 | Disc type rod fastening rotor structure with circumferential tension rod at turbine section for heavy gas turbine |
| EP2565381A3 (en) * | 2011-08-31 | 2017-03-08 | United Technologies Corporation | Assembly and method preventing tie shaft to unscrew |
| JP2015528539A (en) * | 2012-09-07 | 2015-09-28 | シーメンス アクティエンゲゼルシャフト | Method of assembling or disassembling a rotor including a plurality of rotor members of an axial flow turbomachine, and rotor |
| EP2880264A1 (en) * | 2012-09-07 | 2015-06-10 | Siemens Aktiengesellschaft | Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements |
| JP2015527534A (en) * | 2012-09-07 | 2015-09-17 | シーメンス アクティエンゲゼルシャフト | Double nut for joining rotor and two tie rod elements for axial flow turbomachines |
| US20150247406A1 (en) * | 2012-09-07 | 2015-09-03 | Siemens Aktiengesellschaft | Method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor |
| EP2888448A1 (en) * | 2012-09-07 | 2015-07-01 | Siemens Aktiengesellschaft | Method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor |
| EP2927425A1 (en) * | 2014-03-31 | 2015-10-07 | Siemens Aktiengesellschaft | Rotor for a gas turbine having an anti-rotation device for a shaft nut |
| WO2015158513A1 (en) * | 2014-04-15 | 2015-10-22 | Siemens Aktiengesellschaft | Method for assembling and/or disassembling a rotor section of a turbomachine, associated assembly device and rotor disc |
| EP2933433A1 (en) * | 2014-04-15 | 2015-10-21 | Siemens Aktiengesellschaft | Method for assembling and/or disassembling a rotor section of a flow machine, corresponding mounting device and rotor disc |
| JP2016098809A (en) * | 2014-11-21 | 2016-05-30 | ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド | Gas turbine with plurality of tie rods and method of assembling the same |
| US9951687B2 (en) | 2014-11-21 | 2018-04-24 | Doosan Heavy Industries Construction Co., Ltd. | Gas turbine with plurality of tie rods and method of assembling the same |
| EP3023580B1 (en) * | 2014-11-21 | 2021-03-03 | Doosan Heavy Industries & Construction Co., Ltd. | Gas turbine with plurality of tie rods and method of assembling the same |
| FR3039857A1 (en) * | 2015-08-04 | 2017-02-10 | Snecma | METHOD AND DEVICE FOR CLAMPING A ROTOR LINE OF TURBOMACHINE |
| CN110238645A (en) * | 2019-05-31 | 2019-09-17 | 沈阳透平机械股份有限公司 | A kind of turbine rotor spindle mounted device and method |
| CN110238645B (en) * | 2019-05-31 | 2020-07-31 | 沈阳透平机械股份有限公司 | Turbine rotor spindle assembling device and method |
| KR20210070711A (en) * | 2019-12-05 | 2021-06-15 | 두산중공업 주식회사 | Coupling structure for gas turbine and gas turbine comprising the same |
| KR102320481B1 (en) * | 2019-12-05 | 2021-11-02 | 두산중공업 주식회사 | Coupling structure for gas turbine and gas turbine comprising the same |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0718246D0 (en) | 2007-10-31 |
| GB2452932A8 (en) | 2011-08-10 |
| GB2452932B8 (en) | 2011-08-10 |
| GB2452932B (en) | 2009-08-05 |
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