US20140356178A1 - Blade of a turbine - Google Patents
Blade of a turbine Download PDFInfo
- Publication number
- US20140356178A1 US20140356178A1 US14/279,959 US201414279959A US2014356178A1 US 20140356178 A1 US20140356178 A1 US 20140356178A1 US 201414279959 A US201414279959 A US 201414279959A US 2014356178 A1 US2014356178 A1 US 2014356178A1
- Authority
- US
- United States
- Prior art keywords
- blade
- locking pin
- rotor disc
- root portion
- protrusion
- 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
Images
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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
-
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- 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
Definitions
- the present invention relates to a turbine, in particular, to a blade of turbine, more particularly, to a blade with a locking member to make axial fixation of the blade relative to the rotor disc.
- a gas turbine has a rotor assembly which generally includes blades attached to a rotor disc.
- Each blade comprises a root, a platform and an airfoil.
- the root of each blade is usually of a so-called “fir tree” configuration to enable it to be firmly attached to the periphery of the disc and still have room for thermal expansion.
- the “fir tree” attachment of a blade to the rotor disc is effective in restraining the radial and circumferential movements of the blades, relative to the rotor disc, against radial centrifugal forces.
- a conventional solution is applying a tab washer to fix the blade root relative to the slots in the rotor disc.
- the tab washer needs to be bent at assembly, which increases the complexity for the assembly process and may cause errors.
- U.S. Pat. No. 4,349,318 discloses a blade retaining assembly including a continuous wire-type retainer, a generally cylindrical retaining plate and a split retainer ring. Annular grooves or recesses are machined out of the rotor disc and the roots of the blades for accommodating the individual retaining elements.
- EP0,761,930A1 discloses a retention plate carried in radially inner and outer slots preventing axial movement of the blade roots in their slots.
- a locking member is interposed between an adjacent pair of retention plates to prevent their circumferential movement relative to the disc. The locking member in turn interacts with the disc to anchor itself to the disc.
- a blade of turbine comprising an aerofoil, a platform and a root portion configured to be slidingly received in mounting slots of a rotor disc.
- the blade further comprises a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc.
- the locking member is a locking pin disposed between the root portion and the rotor disc, the locking pin comprising a first protrusion to engage with a first groove in the root portion and a second protrusion to engage with a second groove in the rotor disc.
- the first and second protrusions are arranged at one end of the locking pin to be received by the first and second groove respectively.
- the locking pin comprises a third protrusion at the other end thereof to abut on a component arranged next to the blade in the axial direction of the rotor.
- the component comprises a heat shield with an anti-rotation member to engage with the third protrusion of the locking pin.
- the anti-rotation member is sized and positioned so that the anti-rotation member is engaged with the third protrusion of the locking pin as the first and second protrusions of the locking pin are engaged with the first and second grooves respectively.
- the locking member or the locking pin is disposed at the both sides of the root portion.
- the technical solution of the present invention provides a blade with simple and cost effective axial locking system to make axial fixation of the blade relative to the rotor disc, and also a fail-safe solution during assembly process.
- FIG. 1 shows a schematic perspective view of a blade assembly of turbine with a locking pin according to embodiments of the present invention
- FIG. 2 shows a front view of the blade assembly in FIG. 1 ;
- FIG. 3 shows a cross-section side view of the blade assembly.
- FIG. 1 shows a schematic view of a blade assembly of turbine according to embodiments of the present invention.
- the blade 100 comprises an aerofoil 111 , a platform 112 and a root portion 101 .
- the “fir tree” type root portion is configured to be received in the mounting slots of a rotor disc 102 .
- the rotor disc 102 is not shown in FIG. 1 , but can be seen from FIG. 3 , which shows a cross section view of the assembly of the root portion 101 and the rotor disc 102 .
- the blade 100 further comprises a locking member disposed on the root portion 101 and engaged with the rotor disc 102 , so as to make axial fixation of the blade relative to the rotor disc 102 .
- the locking member is embodied as a locking pin 106 as shown in FIG. 1 .
- the locking pin 106 is disposed between the rotor portion 101 and the rotor disc 102 , which can be seen from the cross-section view of FIG. 3 .
- a first protrusion 107 and a second protrusion 108 are respectively disposed on the locking pin 106 in the radial direction.
- a first groove 104 is arranged on the root portion 101 to receive the first protrusion 107 ; a second groove 105 is arranged on the rotor disc 102 to receive the second protrusion 108 .
- the first protrusion 107 and the second protrusion 108 are arranged at one end of the locking pin 106 in the radial direction.
- the first groove 104 and the second groove 105 are respectively formed on the root portion 101 and the rotor disc 102 at the corresponding position to receive the first protrusion 107 and the second protrusion 108 .
- the two protrusions are not necessarily arranged at the same end of the locking pin 106 .
- the protrusions 107 , 108 may also be staggered along the axial direction of the locking pin 106 , as long as they are received in the corresponding grooves respectively.
- a third protrusion 109 is arranged at the other end of the locking pin 106 opposite to the one end where the protrusions 107 , 108 is disposed.
- a heat shield 103 is arranged next to the root portion 101 of the blade in the axial direction.
- the heat shield 103 comprises an anti-rotation member 110 .
- the anti-rotation member 110 is sized and positioned so that it is engaged with the third protrusion 109 of the locking pin 106 as the first and second protrusions 107 and 108 of the locking pin 106 are engaged with the first and second grooves 104 and 105 respectively.
- the locking pin 106 will be inserted between the root portion 101 and the rotor disc 102 .
- the locking pin 106 needs to be rotated by a certain degrees so that the first and second protrusions 107 and 108 can be locked into the corresponding grooves 104 and 105 , respectively.
- the protrusions 107 , 108 and grooves 104 , 105 may not be visible after insertion of the locking pin 106 , it is difficult to evaluate whether the pin is installed in position.
- the anti-rotation member 110 may also function as position element for the locking pin 106 .
- the heat shield 103 will be assembled in axial direction next to the root portion 101 .
- the anti-rotation member 110 will be stuck on the third protrusion 109 .
- the heat shield 103 cannot be assembled in position. Only when the locking pin 106 is rotated into lock position, the heat shield 103 can be installed correctly with the anti-rotation member 110 being engaged with the third protrusion 109 .
- a fail-safe feature for assembling the locking pin is achieved.
- the anti-rotation member may also be arranged on other components than the heat shield as far as the fail-safe feature for assembling the locking pin is achieved.
- the locking pins 106 can be disposed at the both sides of each root portion 101 .
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a blade of turbine having an aerofoil, a platform and a root portion configured to be slidingly received in mounting slots of a rotor disc. The blade further includes a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc. With the technical solution of the present invention, it provides a blade with simple and cost effective axial locking system to make axial fixation of the blade relative to the rotor disc, and also a fail-safe solution during assembly process.
Description
- This application claims priority to European application 13169635.3 filed May 29, 2013, the contents of which are hereby incorporated in its entirety.
- The present invention relates to a turbine, in particular, to a blade of turbine, more particularly, to a blade with a locking member to make axial fixation of the blade relative to the rotor disc.
- A gas turbine has a rotor assembly which generally includes blades attached to a rotor disc. Each blade comprises a root, a platform and an airfoil. The root of each blade is usually of a so-called “fir tree” configuration to enable it to be firmly attached to the periphery of the disc and still have room for thermal expansion. The “fir tree” attachment of a blade to the rotor disc is effective in restraining the radial and circumferential movements of the blades, relative to the rotor disc, against radial centrifugal forces. However, during high speed, high temperature operation of the gas turbine engine, the axial flow of air or gas through the rotor assembly exerts a constant axial force on the blades so as to bias the blade roots axially relative to the “fir tree” slots in the periphery of the rotor disc. In order to restrain the blades against the axial force, it has been common practice to employ various retention systems.
- A conventional solution is applying a tab washer to fix the blade root relative to the slots in the rotor disc. However, the tab washer needs to be bent at assembly, which increases the complexity for the assembly process and may cause errors.
- U.S. Pat. No. 4,349,318 discloses a blade retaining assembly including a continuous wire-type retainer, a generally cylindrical retaining plate and a split retainer ring. Annular grooves or recesses are machined out of the rotor disc and the roots of the blades for accommodating the individual retaining elements.
- EP0,761,930A1 discloses a retention plate carried in radially inner and outer slots preventing axial movement of the blade roots in their slots. A locking member is interposed between an adjacent pair of retention plates to prevent their circumferential movement relative to the disc. The locking member in turn interacts with the disc to anchor itself to the disc.
- It can be seen from above mentioned reference that the current axial retention systems either need further work during the assembly process or have a complex structure, which cause expensive cost of the product and higher likelihood of failures.
- It is an object of the present invention to provide a turbine blade with a simple locking member for axial fixation of the blade relative to the rotor disc.
- It is another object of the present invention to provide a fail-safe solution during assembly process of the locking member.
- The objects are achieved by a blade of turbine, comprising an aerofoil, a platform and a root portion configured to be slidingly received in mounting slots of a rotor disc. The blade further comprises a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc.
- According to one possible embodiment of the present invention, the locking member is a locking pin disposed between the root portion and the rotor disc, the locking pin comprising a first protrusion to engage with a first groove in the root portion and a second protrusion to engage with a second groove in the rotor disc.
- According to one possible embodiment of the present invention, the first and second protrusions are arranged at one end of the locking pin to be received by the first and second groove respectively.
- According to one possible embodiment of the present invention, the locking pin comprises a third protrusion at the other end thereof to abut on a component arranged next to the blade in the axial direction of the rotor.
- According to one possible embodiment of the present invention, the component comprises a heat shield with an anti-rotation member to engage with the third protrusion of the locking pin.
- According to one possible embodiment of the present invention, the anti-rotation member is sized and positioned so that the anti-rotation member is engaged with the third protrusion of the locking pin as the first and second protrusions of the locking pin are engaged with the first and second grooves respectively.
- According to one possible embodiment of the present invention, the locking member or the locking pin is disposed at the both sides of the root portion.
- With the technical solution of the present invention, it provides a blade with simple and cost effective axial locking system to make axial fixation of the blade relative to the rotor disc, and also a fail-safe solution during assembly process.
- The present invention is now to be explained more closely by means of different embodiments and with reference to the drawings.
-
FIG. 1 shows a schematic perspective view of a blade assembly of turbine with a locking pin according to embodiments of the present invention; -
FIG. 2 shows a front view of the blade assembly inFIG. 1 ; and -
FIG. 3 shows a cross-section side view of the blade assembly. -
FIG. 1 shows a schematic view of a blade assembly of turbine according to embodiments of the present invention. Theblade 100 comprises anaerofoil 111, aplatform 112 and aroot portion 101. The “fir tree” type root portion is configured to be received in the mounting slots of arotor disc 102. To show acomplete root portion 101, therotor disc 102 is not shown inFIG. 1 , but can be seen fromFIG. 3 , which shows a cross section view of the assembly of theroot portion 101 and therotor disc 102. - According to an embodiment of the present invention, the
blade 100 further comprises a locking member disposed on theroot portion 101 and engaged with therotor disc 102, so as to make axial fixation of the blade relative to therotor disc 102. - In a preferable embodiment of the present invention, the locking member is embodied as a
locking pin 106 as shown inFIG. 1 . Thelocking pin 106 is disposed between therotor portion 101 and therotor disc 102, which can be seen from the cross-section view ofFIG. 3 . With reference toFIG. 1 andFIG. 2 , afirst protrusion 107 and asecond protrusion 108 are respectively disposed on thelocking pin 106 in the radial direction. Afirst groove 104 is arranged on theroot portion 101 to receive thefirst protrusion 107; asecond groove 105 is arranged on therotor disc 102 to receive thesecond protrusion 108. - In a preferable embodiment of the present invention, the
first protrusion 107 and thesecond protrusion 108 are arranged at one end of thelocking pin 106 in the radial direction. Thefirst groove 104 and thesecond groove 105 are respectively formed on theroot portion 101 and therotor disc 102 at the corresponding position to receive thefirst protrusion 107 and thesecond protrusion 108. However, it should be noticed by those skilled in the art that the two protrusions are not necessarily arranged at the same end of thelocking pin 106. For example, theprotrusions locking pin 106, as long as they are received in the corresponding grooves respectively. - In a preferable embodiment of the present invention, a
third protrusion 109 is arranged at the other end of thelocking pin 106 opposite to the one end where theprotrusions FIG. 1 , aheat shield 103 is arranged next to theroot portion 101 of the blade in the axial direction. Theheat shield 103 comprises ananti-rotation member 110. Theanti-rotation member 110 is sized and positioned so that it is engaged with thethird protrusion 109 of thelocking pin 106 as the first andsecond protrusions locking pin 106 are engaged with the first andsecond grooves - During the assembling process, after the installation of the
blade 100 and therotor disc 102, thelocking pin 106 will be inserted between theroot portion 101 and therotor disc 102. After inserted, thelocking pin 106 needs to be rotated by a certain degrees so that the first andsecond protrusions corresponding grooves protrusions grooves locking pin 106, it is difficult to evaluate whether the pin is installed in position. This issue can be solved by arrangement of theanti-rotation member 110 and its engagement with thethird protrusion 109 of thepin 106 as mentioned above, in which case theanti-rotation member 110 may also function as position element for thelocking pin 106. In particular, after the locking pin is installed, theheat shield 103 will be assembled in axial direction next to theroot portion 101. However, if thelocking pin 106 is not in position, theanti-rotation member 110 will be stuck on thethird protrusion 109. Then, theheat shield 103 cannot be assembled in position. Only when thelocking pin 106 is rotated into lock position, theheat shield 103 can be installed correctly with theanti-rotation member 110 being engaged with thethird protrusion 109. Thus, a fail-safe feature for assembling the locking pin is achieved. - It should be noticed by those skilled in the art that the anti-rotation member may also be arranged on other components than the heat shield as far as the fail-safe feature for assembling the locking pin is achieved.
- Additionally, as shown in
FIG. 3 , the locking pins 106 can be disposed at the both sides of eachroot portion 101. - While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims (8)
1. A blade of turbine, comprising an aerofoil, a platform, a root portion configured to be slidingly received in mounting slots of a rotor disc, and a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc.
2. The blade of claim 1 , wherein the locking member is a locking pin disposed between the root portion and the rotor disc, the locking pin comprising a first protrusion to engage with a first groove in the root portion and a second protrusion to engage with a second groove in the rotor disc.
3. The blade of claim 2 , wherein the first and second protrusion are arranged at one end of the locking pin to be received by the first and second groove respectively.
4. The blade of claim 2 , wherein the locking pin comprises a third protrusion at the other end thereof to abut on a component arranged next to the blade in the axial direction of the rotor.
5. The blade of claim 4 , wherein the component comprises a heat shield with an anti-rotation member to engage with the third protrusion of the locking pin.
6. The blade of claim 5 , wherein the anti-rotation member is sized and positioned so that the anti-rotation member is engaged with the third protrusion of the locking pin as the first and second protrusions of the locking pin are engaged with the first and second grooves respectively.
7. The blade of claim 1 , wherein the locking member is disposed at the both sides of the root portion.
8. The blade of claim 2 , wherein the locking pin is disposed at the both sides of the root portion.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP13169635.3A EP2808490A1 (en) | 2013-05-29 | 2013-05-29 | Turbine blade with locking pin |
EP13169635.3 | 2013-05-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
US20140356178A1 true US20140356178A1 (en) | 2014-12-04 |
Family
ID=48482990
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/279,959 Abandoned US20140356178A1 (en) | 2013-05-29 | 2014-05-16 | Blade of a turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20140356178A1 (en) |
EP (1) | EP2808490A1 (en) |
JP (1) | JP5970020B2 (en) |
KR (1) | KR101642983B1 (en) |
CN (1) | CN104213941B (en) |
RU (1) | RU2585579C2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180179903A1 (en) * | 2016-12-22 | 2018-06-28 | Nuovo Pignone Tecnologie Srl | Turbine blade and locking set |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP7385992B2 (en) * | 2018-12-28 | 2023-11-24 | 川崎重工業株式会社 | Rotating blades and disks |
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US2942842A (en) * | 1956-06-13 | 1960-06-28 | Gen Motors Corp | Turbine blade lock |
US20110176923A1 (en) * | 2010-01-19 | 2011-07-21 | General Electric Company | Seal plate and bucket retention pin assembly |
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US4349318A (en) | 1980-01-04 | 1982-09-14 | Avco Corporation | Boltless blade retainer for a turbine wheel |
JPS60192201U (en) * | 1984-05-30 | 1985-12-20 | 株式会社東芝 | Steam turbine rotor blade fixed structure |
SU1714170A1 (en) * | 1990-02-23 | 1992-02-23 | Ленинградский Кораблестроительный Институт | Arrangement to lock working blades of turbine against axial displacement |
GB9517369D0 (en) | 1995-08-24 | 1995-10-25 | Rolls Royce Plc | Bladed rotor |
US5713721A (en) * | 1996-05-09 | 1998-02-03 | General Electric Co. | Retention system for the blades of a rotary machine |
UA66385C2 (en) * | 2001-01-03 | 2004-05-17 | Центр Науково-Дослідних Та Дослідно-Конструкторських Робіт "Машпроект" Державного Підприємства "Науково-Виробничий Комплекс Газотурбобудування "Зоря"-" Машпроект" | Fixation node of the working blades of the axial turbo-machine rotor and method for assembling it |
US6652237B2 (en) * | 2001-10-15 | 2003-11-25 | General Electric Company | Bucket and wheel dovetail design for turbine rotors |
CN1497131A (en) * | 2002-10-18 | 2004-05-19 | 通用电气公司 | Method and device for preventing damaging blade of gas turbine engine |
US6893224B2 (en) * | 2002-12-11 | 2005-05-17 | General Electric Company | Methods and apparatus for assembling turbine engines |
GB2406144A (en) * | 2003-09-19 | 2005-03-23 | Rolls Royce Plc | Gas turbine engine blade retention system using a key |
JP4869616B2 (en) * | 2005-04-01 | 2012-02-08 | 株式会社日立製作所 | Steam turbine blade, steam turbine rotor, steam turbine using the same, and power plant |
DE602005005988T2 (en) * | 2005-08-12 | 2009-05-20 | Siemens Aktiengesellschaft | Turbine for a thermal power plant with holding device |
RU2330163C1 (en) * | 2006-11-01 | 2008-07-27 | Открытое акционерное общество "Силовые машины-ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (ОАО "Силовые машины") | Gas turbine wheel |
US8061995B2 (en) * | 2008-01-10 | 2011-11-22 | General Electric Company | Machine component retention |
US8714929B2 (en) * | 2010-11-10 | 2014-05-06 | General Electric Company | Turbine assembly and method for securing a closure bucket |
RU2557826C2 (en) * | 2010-12-09 | 2015-07-27 | Альстом Текнолоджи Лтд | Gas turbine with axial hot air flow, and axial compressor |
US20120177498A1 (en) * | 2011-01-07 | 2012-07-12 | General Electric Company | Axial retention device for turbine system |
US8840375B2 (en) * | 2011-03-21 | 2014-09-23 | United Technologies Corporation | Component lock for a gas turbine engine |
US8727733B2 (en) * | 2011-05-26 | 2014-05-20 | General Electric Company | Gas turbine compressor last stage rotor blades with axial retention |
-
2013
- 2013-05-29 EP EP13169635.3A patent/EP2808490A1/en not_active Withdrawn
-
2014
- 2014-05-16 US US14/279,959 patent/US20140356178A1/en not_active Abandoned
- 2014-05-21 RU RU2014120542/02A patent/RU2585579C2/en not_active IP Right Cessation
- 2014-05-26 KR KR1020140062809A patent/KR101642983B1/en active IP Right Grant
- 2014-05-29 JP JP2014110844A patent/JP5970020B2/en not_active Expired - Fee Related
- 2014-05-29 CN CN201410233327.3A patent/CN104213941B/en not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
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US2942842A (en) * | 1956-06-13 | 1960-06-28 | Gen Motors Corp | Turbine blade lock |
US20110176923A1 (en) * | 2010-01-19 | 2011-07-21 | General Electric Company | Seal plate and bucket retention pin assembly |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20180179903A1 (en) * | 2016-12-22 | 2018-06-28 | Nuovo Pignone Tecnologie Srl | Turbine blade and locking set |
US10669868B2 (en) * | 2016-12-22 | 2020-06-02 | Nuovo Pignone Tecnologie Srl | Turbine blade and locking set |
Also Published As
Publication number | Publication date |
---|---|
KR20140140497A (en) | 2014-12-09 |
RU2585579C2 (en) | 2016-05-27 |
JP5970020B2 (en) | 2016-08-17 |
RU2014120542A (en) | 2016-01-10 |
JP2014231839A (en) | 2014-12-11 |
EP2808490A1 (en) | 2014-12-03 |
CN104213941B (en) | 2016-03-23 |
CN104213941A (en) | 2014-12-17 |
KR101642983B1 (en) | 2016-07-27 |
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