EP1028228A1 - Dispositif de refroidissement de plate-forme d'aube rotorique de turbine - Google Patents

Dispositif de refroidissement de plate-forme d'aube rotorique de turbine Download PDF

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Publication number
EP1028228A1
EP1028228A1 EP99102532A EP99102532A EP1028228A1 EP 1028228 A1 EP1028228 A1 EP 1028228A1 EP 99102532 A EP99102532 A EP 99102532A EP 99102532 A EP99102532 A EP 99102532A EP 1028228 A1 EP1028228 A1 EP 1028228A1
Authority
EP
European Patent Office
Prior art keywords
platform
rotor blade
turbine rotor
plate
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.)
Withdrawn
Application number
EP99102532A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP99102532A priority Critical patent/EP1028228A1/fr
Publication of EP1028228A1 publication Critical patent/EP1028228A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the present invention relates to a turbine blade, especially for a gas turbine, with a foot for attachment on a rotor of a turbine and a blade for flow around through a working medium, the turbine blade a platform to limit a channel for that Has working medium and for cooling radially inward Platform at least one baffle plate is arranged.
  • the turbine blade includes one Foot for attachment to a rotor of the turbine, a blade for flow around a working medium and a platform for Limit a channel for the working medium.
  • a perforated wall element arranged as Impact heat sink is called.
  • About recesses in the A baffle coolant enters and hits the coolant side of the platform facing away from the working medium.
  • cooling of the platform is achieved.
  • the baffle plate can be welded onto the platform.
  • this welded connection is used for the turbine blades used materials, especially at single-crystalline materials, very critical. Due to the The structure is locally deformed during thermal stress during welding and shows discontinuities. In addition, in Area of the weld seam cracks that extend into the Extend the platform. This will increase the strength the turbine blades are reduced.
  • the object of the present invention is therefore a turbine blade Provide easy attachment of the baffle plate and easy assembly of the Turbine rotor blades on the rotor of the turbine are possible.
  • this object is achieved with a turbine blade of the type mentioned in that the Impact cooling plate when the rotor is at a standstill opposite the platform movable and due to the rotation of the rotor Centrifugal force is immovably pressed to the platform.
  • the turbine blade When the rotor is at a standstill, the turbine blade is cooled not mandatory.
  • the baffle plate must then do not rest on the platform in a defined position. in the The baffle cooling plate is operated by the centrifugal force to the outside crowded, pressed against the platform and thereby immobile locked. The only while the turbine is operating Required cooling by means of the baffle plate is guaranteed. A structural change by welding the Baffle plate does not occur. Also inserting intricately shaped inserts with a complex assembly is no longer required.
  • a loss protection for the baffle plate provided. This protection against loss lasts the baffle plate in one when the rotor is at a standstill given space. A falling or an inadmissible Moving the baffle plate from one on the top the turbine blade located on the rotor is prevented. As soon as the turbine starts up again, the baffle cooling plate again due to the centrifugal force Platform pressed on.
  • the opposite is Side of the baffle plate between a contact surface the platform and a damping element added.
  • damping elements are between in known turbines the individual turbine blades to seal the Channel for the working medium already exists.
  • the baffle cooling plate can therefore reliably use on both sides without additional components are held.
  • the baffle cooling plate from a shielding plate is advantageous covered. This shielding plate shields the impact cooling area the platform from the other components of the rotor.
  • the shielding plate is when the rotor is at a standstill in relation to the turbine blade movable and on rotation of the rotor to the turbine blade pressed immovable.
  • the shield can thus like the baffle plate without complicated inserts and without Structural changes are attached.
  • the opposite is Side of the baffle plate between a contact surface the platform and the shield plate.
  • the baffle cooling plate is also reliable with this construction without using other components in a predeterminable Space area kept.
  • the baffle cooling plate and the shield plate has an outlet for Coolant provided.
  • the shielding plate and the platform define one of the coolant in the turbine blade charged room. Due to the baffle cooling plate very good cooling of the platform ensured.
  • Loss protection for the shielding plate is advantageous intended.
  • the protection against loss also holds the shielding plate when the rotor is at a standstill in a given area. Falling or unreliable shifting will be prevented.
  • the shielding plate engages with one side in a receptacle of the turbine blade on.
  • the shielding plate can thus like the impact cooling plate reliable on this side without the use of additional components being held.
  • the opposite side is of the shield plate between a contact surface of the platform and added a damping element.
  • the complete one Fixing the shielding plate can therefore as with the baffle cooling plate done without the use of additional components.
  • the Inclusion of the turbine blade and the damping element serve as a protection against loss for the shielding plate.
  • the shielding plate can be like the impact cooling plate movable with respect to the platform when the rotor is stationary be and immobile when the rotor rotates due to centrifugal force be pressed.
  • the shield plate on the turbine blade there is between the contact surfaces for the shield plate on the turbine blade and the shielding sheet a layer of easily deformable Material arranged.
  • this material due to the centrifugal force deforms and seals any Leaks from.
  • the coolant is thus reliably lossless directed to the baffle plate and onto the platform.
  • the layer is on the shielding plate or attached to the contact surfaces.
  • the Attaching to the shielding plate simplifies the construction the turbine blade. As soon as the layer on the contact surfaces the turbine blade is attached can be different Shielding plates are used. Moreover the shield can be changed easily and inexpensively become.
  • the platform advantageously has support knobs or support ribs to support the baffle plate. This will make an inadmissible Deflection of the baffle plate when the Avoided rotors under the influence of centrifugal force. At the same time the baffle cooling plate can be made comparatively thin become.
  • Figure 1 shows a schematic longitudinal section through a gas turbine 10 with a housing 11 and one in the housing rotatably mounted rotor 12.
  • the housing 11 is with turbine guide vanes 13 provided radially inward to the rotor 12 protrude.
  • Turbine rotor blades 14 are attached to the rotor 12, which protrude radially outward to the housing 11.
  • a channel 15 for a working medium Between housing 11 and the rotor 12 is formed a channel 15 for a working medium.
  • the working medium flows through the channel in the direction from right to left along the three positions A, B and C.
  • the inlet temperature of the working medium chosen very large to achieve the highest possible efficiency to obtain.
  • the temperature in point A can for example 1100 ° C, in point B 1000 ° C and in point C 930 ° C. This high temperatures require cooling of the turbine guide vanes 13 and the turbine blades 14, which are schematic
  • Cooling air is used as the cooling medium, that of the gas turbine 10 upstream compressor is removed.
  • the cooling air is through suitable, not shown holes in Housing 11 and in the rotor 12 to the turbine guide vanes 13 and the turbine blades 14 out. It flows through the Turbine guide vanes 13 and turbine rotor blades 14 and finally exits into channel 15.
  • it is Cooling is not provided over the entire length of the rotor 12, but only in the area of the first turbine guide vane 13 and the first turbine blade 14. The reason for this is the falling temperature of the working medium in the channel 15.
  • FIG. 2 shows a section along the line II-II of Figure 1.
  • Each of the turbine blades 14 has a foot 16 for attachment to the rotor 12 of the gas turbine 10 on. It is also a blade 18 for flow around provided by the working medium. Every turbine blade 14 has a platform 17 for limiting the channel 15 for the working medium.
  • For cooling is the radially inward Platform 17 left and right of the foot 16 an impact baffle 19 arranged.
  • Each of the baffle plate 19 is covered by a shielding plate 22. Between the baffle plate 19 and the associated shielding plate 22 is an outlet opening 30 provided for a coolant. Is further between two spaced apart turbine blades 14, a damping element 25 is arranged.
  • Each baffle cooling plate 19 is opposite when the rotor 12 is at a standstill the platform is movable and when the rotor 12 rotates due to the centrifugal force on the platform 17 immobile in Direction of arrow 33 pressed.
  • the shielding plates 22 are also when the rotor 12 is stationary and movable when the Rotors 12 pressed immovably due to the centrifugal force.
  • FIG 3 shows an enlarged view of the inclusion of a Baffle cooling plate 19 and a shielding plate 22 on a turbine blade 14. It is a loss protection for that Baffle cooling plate provided, which from the shield plate 22 and a receptacle 32 in the turbine blade 14.
  • the Impact cooling plate 19 engages with one side in the receptacle 32 the turbine blade 14.
  • the opposite side is between a contact surface 21 of the platform 17 and the Shield 22 added.
  • the shield plate 22 engages with one side in a receptacle 38 of the turbine blade 14 a.
  • the opposite side is between one Contact surface 24 of the platform 17 and the damping element 25 added.
  • the baffle plate 19 is due to the centrifugal force in the arrow direction 33 against contact surfaces 20, 21 on the Platform 17 pressed.
  • the shield 22 is also from the centrifugal force in the direction of arrow 33 against contact surfaces 23, 24 pressed.
  • the baffle cooling plate 19 and the shielding plate 22 are therefore due to the rotation of the rotor 12 in operation Centrifugal force immobile in relation to platform 17.
  • the baffle cooling plate 19 When the rotor 12 is at a standstill, the baffle cooling plate 19 is opposite the platform 17 movable. A complete fall is by the approach 27 of the turbine blade 14th and prevents the shielding plate. The baffle cooling plate 19 is therefore, even when the rotor 12 is at a standstill Space area kept. As soon as the rotor 12 starts again, the baffle plate 19 is again due to the centrifugal force immovably pressed against the contact surfaces 20, 21 of the platform 17. The shield plate 22 is also through the receptacle 38 the turbine blade 14 and the damping element 25 reliably kept in a given area. At Standstill of the rotor 12 serve the receptacle 38 and the damping element 25 as loss protection for the shielding plate 22.
  • the shielding plate 22 can therefore only in a predetermined Move room area.
  • the rotor 12 starts up the shielding plate 22 immovably on the contact surfaces 23, 24 the turbine blade 14 pressed.
  • the damping element 25 rests on contact surfaces 26 of the turbine rotor blade 14. It is automatically between the contact surfaces 26 the two adjacent turbine blades 14 centered. At the same time, the damping element 25 is supported on the shielding plates 22 from.
  • a coolant is used to cool the platform 17 Outlet opening 30 between the baffle plate 19 and the Shield 22 initiated.
  • the coolant 30 flows through Recesses 29 in the baffle cooling plate 19 in an intermediate space 31 between the baffle cooling plate 19 and the platform 17th There it meets the platform 17 essentially vertically on. Then the coolant is not shown Drilled holes.
  • the shield 22 prevents an uncontrolled spread of the coolant and limited the cooling effect as intended on the platform 17. This reduces the consumption of coolant.
  • FIG 4 shows a view like Figure 3 in another embodiment. The same was used for the same or similar components Reference numerals as used in Figure 3.
  • the baffle cooling plate 19 engages with one side in the receptacle 32 of the turbine blade 14. A fall of the baffle plate 19 when the rotor 12 is at a standstill through the approach 27 prevented.
  • the opposite side of the baffle plate 19 is between the contact surface 21 of the platform 17th and the damping element 25 added.
  • the damping element 25 and the receptacle 32 provide loss protection for the Baffle cooling plate 19 ready.
  • the captive 25, 32 holds the baffle cooling plate 19 even when the rotor 12 is at a standstill a given area.
  • the baffle cooling plate 19 is movable relative to the platform 17. It is only due to the rotation of the rotor 12 the centrifugal force in the direction of arrow 33 immovable to the platform 17 pressed.
  • Figures 5 and 6 show an enlarged view of the Detail X from Figure 3 in two different embodiments.
  • there is one layer 34, 35 made of easily deformable material between the shielding plate 22 and the contact surface 23 on a shoulder 28 of the Turbine rotor blade 14 is provided.
  • this layer 34 on the shielding plate 22 is attached.
  • the soft layer 35 is attached to the contact surface 23. The opposite side of the shield plate 22 is trained accordingly.
  • the shielding plate 22 When the rotor 12 rotates, the shielding plate 22 is covered by the Centrifugal force with the soft layer 34, 35 against the contact surface 23 pressed. Here, the soft layer 34, 35 deformed so that any existing leaks are eliminated become. The coolant flowing through the outlet opening 30 emerges, is thus reliably in the intended cooling area held.
  • the creep resistance is required to completely displace layer 34, 35 from the space between the contact surfaces 23, 24 and to prevent the shield plate 22 due to the high centrifugal force.
  • FIGs 7 and 8 show two embodiments of the system of the baffle plate 19 on the platform 17.
  • a support of the baffle cooling plate 19 is provided.
  • FIG 7 are in the space 31 arranged, spatially separated from each other Support knobs 36 used.
  • Figure 8 shows in the space 31 arranged support ribs 37.
  • the support ribs 37 can in some areas be broken so that no subdivision of the Intermediate space 31 takes place.
  • Both the support knobs 36 and the support ribs 37 support the baffle plate 19 during rotation of the rotor 12. This will result in an impermissible deflection of the baffle plate 19 when the rotor 12 rotates under the Influence of centrifugal force avoided.
  • Baffle cooling plate 19 are comparatively thin.
  • the subject of the present invention enables rapid and easy attachment of the baffle plate 19 to the Platforms 17 of the turbine blades 14. A welding the baffle plate 19 is not required, so that a Structural change of the turbine blades 14 reliably is avoided.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99102532A 1999-02-10 1999-02-10 Dispositif de refroidissement de plate-forme d'aube rotorique de turbine Withdrawn EP1028228A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP99102532A EP1028228A1 (fr) 1999-02-10 1999-02-10 Dispositif de refroidissement de plate-forme d'aube rotorique de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99102532A EP1028228A1 (fr) 1999-02-10 1999-02-10 Dispositif de refroidissement de plate-forme d'aube rotorique de turbine

Publications (1)

Publication Number Publication Date
EP1028228A1 true EP1028228A1 (fr) 2000-08-16

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EP99102532A Withdrawn EP1028228A1 (fr) 1999-02-10 1999-02-10 Dispositif de refroidissement de plate-forme d'aube rotorique de turbine

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002050402A1 (fr) * 2000-12-19 2002-06-27 General Electric Company Systeme de refroidissement par impact de jet pour plate-forme d'aube de turbine
EP1249575A1 (fr) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Aube de turbine
EP1413715A1 (fr) 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Dispositif de refroidissement pour une plate-forme d'une aube d'une turbine à gaz
WO2004038179A1 (fr) * 2002-10-24 2004-05-06 Pratt & Whitney Canada Corp. Plate-forme de pales refroidie passivement
EP1621727A1 (fr) * 2004-07-30 2006-02-01 General Electric Company Aube de rotor de turbine et rotor de moteur à turbine à gaz comportant de telles aubes
DE102006004437A1 (de) * 2005-05-27 2006-11-30 Mitsubishi Heavy Industries, Ltd. Plattform einer Laufschaufel einer Gasturbine, Verfahren zur Herstellung einer Laufschaufel, Dichtungsplatte und Gasturbine
JP2007154898A (ja) * 2005-12-08 2007-06-21 General Electric Co <Ge> ダンパ冷却タービン翼
GB2496293A (en) * 2011-10-28 2013-05-08 Snecma Turbine cooling
EP2728114A1 (fr) * 2012-10-31 2014-05-07 Siemens Aktiengesellschaft Dispositif de refroidissement de plate-forme pour une aube de turbomachine et aube pour turbomachine
US8807942B2 (en) 2010-10-04 2014-08-19 Rolls-Royce Plc Turbine disc cooling arrangement
EP3192971A1 (fr) * 2016-01-12 2017-07-19 United Technologies Corporation Pale de turbine à gaz avec refroidissement de plate-forme

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2628807A1 (de) 1975-06-30 1977-01-27 Gen Electric Prallkuehlsystem
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2628807A1 (de) 1975-06-30 1977-01-27 Gen Electric Prallkuehlsystem
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5415526A (en) * 1993-11-19 1995-05-16 Mercadante; Anthony J. Coolable rotor assembly

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002050402A1 (fr) * 2000-12-19 2002-06-27 General Electric Company Systeme de refroidissement par impact de jet pour plate-forme d'aube de turbine
CZ300480B6 (cs) * 2000-12-19 2009-05-27 General Electric Company Turbínová lopatka a zpusob chlazení její základny
KR100814168B1 (ko) * 2000-12-19 2008-03-14 제너럴 일렉트릭 캄파니 터빈 버킷 및 터빈 버킷 플랫폼의 냉각 방법
EP1249575A1 (fr) * 2001-04-12 2002-10-16 Siemens Aktiengesellschaft Aube de turbine
CN100334326C (zh) * 2002-10-21 2007-08-29 西门子公司 透平以及动叶片
EP1413715A1 (fr) 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Dispositif de refroidissement pour une plate-forme d'une aube d'une turbine à gaz
US7059835B2 (en) 2002-10-21 2006-06-13 Siemens Aktiengesellschaft Turbine, in particular a gas turbine, and a blade
WO2004038179A1 (fr) * 2002-10-24 2004-05-06 Pratt & Whitney Canada Corp. Plate-forme de pales refroidie passivement
US6832893B2 (en) 2002-10-24 2004-12-21 Pratt & Whitney Canada Corp. Blade passive cooling feature
EP1621727A1 (fr) * 2004-07-30 2006-02-01 General Electric Company Aube de rotor de turbine et rotor de moteur à turbine à gaz comportant de telles aubes
JP2009047177A (ja) * 2005-05-27 2009-03-05 Mitsubishi Heavy Ind Ltd プラットフォームを有するガスタービン動翼およびその形成方法
DE102006004437A1 (de) * 2005-05-27 2006-11-30 Mitsubishi Heavy Industries, Ltd. Plattform einer Laufschaufel einer Gasturbine, Verfahren zur Herstellung einer Laufschaufel, Dichtungsplatte und Gasturbine
JP2007154898A (ja) * 2005-12-08 2007-06-21 General Electric Co <Ge> ダンパ冷却タービン翼
EP1795703A3 (fr) * 2005-12-08 2008-04-16 General Electric Company Amortisseur pour une plateforme refroidie d'aube de turbine
US8807942B2 (en) 2010-10-04 2014-08-19 Rolls-Royce Plc Turbine disc cooling arrangement
GB2496293A (en) * 2011-10-28 2013-05-08 Snecma Turbine cooling
GB2496293B (en) * 2011-10-28 2015-11-04 Snecma A turbine wheel for a turbine engine
EP2728114A1 (fr) * 2012-10-31 2014-05-07 Siemens Aktiengesellschaft Dispositif de refroidissement de plate-forme pour une aube de turbomachine et aube pour turbomachine
EP3192971A1 (fr) * 2016-01-12 2017-07-19 United Technologies Corporation Pale de turbine à gaz avec refroidissement de plate-forme
US10082033B2 (en) 2016-01-12 2018-09-25 United Technologies Corporation Gas turbine blade with platform cooling

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