EP2372085A2 - Internal reaction steam turbine cooling arrangement - Google Patents

Internal reaction steam turbine cooling arrangement Download PDF

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Publication number
EP2372085A2
EP2372085A2 EP10195081A EP10195081A EP2372085A2 EP 2372085 A2 EP2372085 A2 EP 2372085A2 EP 10195081 A EP10195081 A EP 10195081A EP 10195081 A EP10195081 A EP 10195081A EP 2372085 A2 EP2372085 A2 EP 2372085A2
Authority
EP
European Patent Office
Prior art keywords
rotor
stage
dovetailed
drum
bucket
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Withdrawn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
EP10195081A
Other languages
German (de)
English (en)
French (fr)
Inventor
Bhaskar Mani
Vasanth Muralidharan
Vishwas K. Pandey
Vemula Gopinath Upendra Prabhu Nath
Sulficker Ali
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2372085A2 publication Critical patent/EP2372085A2/en
Withdrawn legal-status Critical Current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
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside 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
    • F01D5/32—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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the invention generally relates to turbomachine rotors. More specifically, the present disclosure relates to cooling of steam turbine rotors.
  • a rotor of a turbomachine includes a rotor drum disposed at a central axis.
  • a plurality of dovetailed buckets for a stage of the turbomachine are provided.
  • the plurality of dovetailed buckets are secured to the rotor drum at mating surfaces within corresponding dovetailed slots cut in the rotor drum.
  • At least one cooling passage is formed within the rotor drum for the stage of the turbomachine.
  • a low pressure sink disposed at an upstream end of the rotor drum is receptive of a coolant flow through the cooling passage.
  • a multi-stage steam turbine includes a stator disposed at a central axis and a rotor disposed radially inboard of the stator.
  • the rotor includes a rotor drum and a plurality of dovetailed buckets for a stage of the steam turbine.
  • the plurality of dovetailed buckets are secured to the rotor drum at mating surfaces within a corresponding dovetailed slots cut in the rotor.
  • At least one cooling passage is formed within the rotor drum for the stage of the turbomachine.
  • a low pressure sink disposed at an upstream end of the rotor is receptive of a coolant flow through the cooling passage.
  • a method for installing axial entry dovetailed buckets into dovetail slots of a stage of a drum rotor includes inserting twist lock devices into an axial through-hole in a base of a dovetail slot of a stage of a drum rotor for each of the dovetailed buckets.
  • a half-head of a front head of the twist lock device is oriented in an inward radial direction to allow entry of the dovetailed bucket into the dovetail slot.
  • a spacer is temporarily installed in a space in the drum rotor between a stage and a succeeding stage.
  • the dovetailed bucket is fully inserted into the dovetail slot of the stage of the rotor drum.
  • the half-head of the front head of the twist-lock device is oriented in an outward radial direction to lock the bucket in place. The spacer is removed.
  • the present invention has many advantages including providing cooling for a reaction stage of a drum rotor in order to preserve life of the rotor and permit the rotor to be formed with standard rotor materials instead of expensive materials that are temperature resistant.
  • the first stage of a rotor for a steam turbine is generally exposed to the highest temperatures and pressures. Therefore it is desirable to provide cooling in particular for the first stage section of the rotor drum. Due to negative root reaction in the first stage, the temperature out the outlet of the stage bucket will be cooler than the inlet to the stage bucket but the pressure at the outlet of the stage bucket will be higher than the pressure at the inlet.
  • steam at the outlet of the stage bucket at a higher pressure than the inlet to the stage bucket may be used to force the cooler steam downstream from the bucket through a path which cools the first stage of the drum rotor and which discharges to a low pressure sink.
  • an arrangement is provided to extract a lower temperature steam downstream from a stage in a reaction turbine with drum-rotor construction by a cooling passage that is formed by arranging axial entry dovetails over the axial slots cut on the drum-rotor.
  • the cooling passage is formed within the drum-rotor at the mating surfaces of the drum-rotor and the dovetail. This will allow the cooling flow to pass through the dovetails and later mix with the flow leaking to the packing side from the downstream side of the first nozzle. This mix flow will flow from the packing side and cool the drum-rotor.
  • the above-described arrangement may provide for performance gain by allowing more flow to pass over the first stage bucket than a standard design.
  • the arrangement also allows cooling directed to the high temperature zones of a reaction/impulse rotor. Further with the advantageous cooling, there is no need for costly material at higher operating temperature. Additionally, no new significant major components need to be added to implement the cooling.
  • FIG. 1 Shown in FIG. 1 is an embodiment of a turbomachine, such as a steam turbine with an inventive cooling mechanism for the rotor.
  • the steam turbine 10 includes a rotor 12 rotatably disposed at an axis 14 of the steam turbine.
  • a first stage of the turbine includes a nozzle buckets 16 are secured in a plurality of bucket slots 18 in a rotor drum 13 and are typically arranged in a number of rows, or stages, that extend around a circumference of the rotor 12 at axial locations along the rotor 12.
  • a plurality of stationary nozzles 20 are secured in a plurality of nozzle slots 22 in a stator 24 of the steam turbine 10.
  • the nozzle slots 22 may be located in an inner carrier of the stator 24.
  • the nozzles 20 are arranged in circumferential stages that are located between stages of buckets 16.
  • the rotor 12 and the stator 24 defme a primary flowpath 26 therebetween.
  • a fluid, for example, steam is directed from steam inlet 23 along the primary flowpath 26, which urges rotation of the rotor 12 about the axis 14.
  • FIG. 2 illustrates a radial view of a sector of a first stage 30 with axial female tree dovetail slots 32 cut in the rotor drum 13.
  • a channel 34 cut to accept a twist lock device (not shown) that is used to axially lock in place the male tree dovetail 50 of the buckets 16.
  • FIG. 3 illustrates a side view of a twist lock device 40 adapted for holding axial entry dovetailed buckets in axial dovetailed slots.
  • the twist lock device 40 includes a center pin 42 with heads 44 at each end of the center pin.
  • the head 44 at a first end of the center pin 42 is formed as a half head 46 and includes a staking tab.
  • the head 44 at the second end of the center pin 42 includes a full head 48.
  • the channel 34 in the rotor is sized for the center pin.
  • the length 43 of the center pin 42 is set to match the channel with the half head 46 outside the front face of the rotor and second head 48 of the pin outside the downstream face of the rotor stage.
  • the twist lock device 40 Before the buckets are installed, the twist lock device 40 is positioned such that the half head 46 is oriented in the inward radial direction. The twist lock device 40 is then lowered into the channel 34 below the female dovetail slot 32 into the rotor drum. FIG. 4 illustrates the twist lock device 40 in place within the channel 34 of female dovetail slot 32 in preparation for axial insertion of a bucket male tree dovetail. If the twist lock device 40 is inserted into wheel (rotor) dovetail with the half head 46 in an outward radial orientation, the half head 46 will block sliding the axial entry male dovetail 50 of the bucket inside the wheel (rotor) slot.
  • the axial entry male dovetail 50 of the bucket is then slid into the wheel (rotor) slot in the axial direction.
  • the twist lock device 40 is rotated by 180 degrees such the half head 46 oriented outward radially and flat surface 45 is radially inward as shown in FIG. 5
  • the head 46 for the twist lock 20 will be bent inside a wheel staking groove 47 in the wheel (rotor) face 49 as shown in FIG. 6 .
  • Insufficient space is available on the downstream side for staking so the twist lock device 40 has a full cylindrical head 48 on the downstream side. Staking of the twist lock device 40 prevents axial movement of the installed bucket.
  • Other buckets may be installed in a similar manner.
  • annular space downstream of the stage section is also cut into the rotor drum to allow a space for the cutting tool to be removed.
  • a spacer ring forming at least a sector of the removed downstream annular space is installed to facilitate installation of the buckets. The thickness of the spacer ring is set to limit the insertion of the male dovetail for the bucket, thereby establishing proper axial orientation. After the buckets have been inserted the proper axial distance and locked in place, the spacer is removed.
  • FIG. 7 illustrates an expanded radial view of a cooling space 70 between the male dovetail 50 of the first stage bucket and a complimentary male projection of the rotor drum 13.
  • the male dovetails include an expanded space 75 at an outer end that provides the axial channel for the flow of cooling steam. The channel discharges into a low-pressure channel downstream that will be described in greater detail below.
  • FIG. 8 illustrates a cutaway axial view of a cooling path 70 for a rotor drum 13 with axial entry dovetailed bucket 116 installed rotor drum 13.
  • the annular space 60 downstream from the bucket includes the spacer 65 (shown prior to removal).
  • the staked twist lock device 40 axially holds the male dovetail 50 ( FIG. 6 ) of the bucket 116 in place within the rotor drum 13.
  • FIG. 8 also illustrates the axial flow channel 70 for cooling steam 72.
  • the cooling steam 72 is received from the annular space 60 downstream of the reaction stage where, for a reaction stage, the pressure is higher than the upstream side but the steam temperature is substantially cooler.
  • the cooling steam 72 may pass through the axial space 70 between the male dovetail of the bucket and the female dovetail cut into the drum rotor.
  • FIG. 9 illustrates a reaction first reaction stage 110 with an axial entry dovetailed bucket 116.
  • the bucket 116 with male dovetail 50 is disposed between an upstream first stage nozzle 114 and a downstream second stage nozzle 118.
  • the dovetailed bucket 116 is installed axially in the dovetailed slots in the rotor drum 13.
  • the nozzle 114, 118 may be supported by an outer casing (not shown).
  • the nozzles 114, 118 may include various seals mounted on end shrouds 27 to prevent leakage past the nozzle blades 115, 119.
  • the seals may include tooth seals, J-seals, and labyrinth seals.
  • the axial channel 70 through the space between the male dovetail of the bucket and the slot of the drum rotor may direct the downstream cooling steam to the low-pressure channel leakoff discharge path 140.
  • the labyrinth seal 132 on the first stage nozzle 114 prevents higher pressure from the nozzle block 23 in the downstream leakoff path. The higher pressure from the nozzle block 23 could prevent the cooling flow through the cooling path.
  • the tooth seal or the J-seal may limit leakage between the first stage nozzle 114 and the first stage bucket 116 from entering the leakoff path 140 and thereby limiting cooling flow 72.
  • first stage tangential entry buckets 150 with blade 151 in rotor drum 13 of rotor 12 is disposed between first stage nozzle 114 with blade 115 and second stage nozzle 118 with blade 119.
  • the bucket 150 dovetail 153 may be provided with a cooling passage that utilizes higher pressure steam P2 165 downstream from the bucket 150 of a reaction stage 110 to cool the rotor drum 13 as illustrated in FIG. 10 .
  • An axial cooling passage 155 is provided between the bucket 150 and the next nozzle 118.
  • the cooling passage 155 through root 180 of bucket 150 again discharges cooling steam to the low-pressure leakoff discharge path 140. Seals 131 and 132 limit leakage from steam inlet 23 and from space between first stage nozzle 114 and first stage bucket 150 from entering the leakoff path 140 and thereby limiting cooling flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10195081A 2009-12-30 2010-12-15 Internal reaction steam turbine cooling arrangement Withdrawn EP2372085A2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/649,470 US20110158819A1 (en) 2009-12-30 2009-12-30 Internal reaction steam turbine cooling arrangement

Publications (1)

Publication Number Publication Date
EP2372085A2 true EP2372085A2 (en) 2011-10-05

Family

ID=44187797

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10195081A Withdrawn EP2372085A2 (en) 2009-12-30 2010-12-15 Internal reaction steam turbine cooling arrangement

Country Status (4)

Country Link
US (1) US20110158819A1 (ja)
EP (1) EP2372085A2 (ja)
JP (1) JP2011137455A (ja)
RU (1) RU2010153518A (ja)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9194244B2 (en) * 2013-02-25 2015-11-24 General Electric Company Drum rotor dovetail component and related drum rotor system
US9353636B2 (en) 2013-06-06 2016-05-31 Siemens Energy, Inc. Process for replacing a bolted-on nozzle block coupled to a nozzle chamber in a steam turbine
US9702261B2 (en) 2013-12-06 2017-07-11 General Electric Company Steam turbine and methods of assembling the same
US9382801B2 (en) 2014-02-26 2016-07-05 General Electric Company Method for removing a rotor bucket from a turbomachine rotor wheel
US9506357B1 (en) 2015-12-08 2016-11-29 General Electric Company Turbomachine staking tool

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2454580A (en) * 1943-03-18 1948-11-23 Gen Electric Method of manufacturing bladed rotors
GB996729A (en) * 1963-12-16 1965-06-30 Rolls Royce Improvements relating to turbines and compressors
PL90863B1 (ja) * 1974-04-12 1977-02-28
RU2182976C2 (ru) * 1996-06-21 2002-05-27 Сименс Акциенгезелльшафт Турбинный вал, а также способ охлаждения турбинного вала
US6416286B1 (en) * 2000-12-28 2002-07-09 General Electric Company System and method for securing a radially inserted integral closure bucket to a turbine rotor wheel assembly having axially inserted buckets
US7488153B2 (en) * 2002-07-01 2009-02-10 Alstom Technology Ltd. Steam turbine
EP1452688A1 (de) * 2003-02-05 2004-09-01 Siemens Aktiengesellschaft Dampfturbinenrotor sowie Verfahren und Verwendung einer aktiven Kühlung eines Dampfturbinenrotors
US7155800B2 (en) * 2005-02-24 2007-01-02 General Electric Company Automated seal strip assembly method and apparatus for rotary machines
US8096748B2 (en) * 2008-05-15 2012-01-17 General Electric Company Apparatus and method for double flow turbine first stage cooling

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Also Published As

Publication number Publication date
JP2011137455A (ja) 2011-07-14
US20110158819A1 (en) 2011-06-30
RU2010153518A (ru) 2012-07-10

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