EP3134621A1 - Aube de turbine et turbine - Google Patents

Aube de turbine et turbine

Info

Publication number
EP3134621A1
EP3134621A1 EP15725320.4A EP15725320A EP3134621A1 EP 3134621 A1 EP3134621 A1 EP 3134621A1 EP 15725320 A EP15725320 A EP 15725320A EP 3134621 A1 EP3134621 A1 EP 3134621A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
turbine blade
turbine
main channel
hollow guide
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
Application number
EP15725320.4A
Other languages
German (de)
English (en)
Other versions
EP3134621B1 (fr
Inventor
David Johnson
Fathi Ahmad
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP3134621A1 publication Critical patent/EP3134621A1/fr
Application granted granted Critical
Publication of EP3134621B1 publication Critical patent/EP3134621B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades

Definitions

  • Turbine blade and turbine The invention relates to a turbine blade having an internal ⁇ cooled turbine blade, which embodied a portion extending in the longitudinal direction of the turbine blade cooling air main channel at least to cooling air from a cylinder disposed in egg ⁇ nem region of a turbine blade root cooling air passage inlet in the direction of a turbine blade tip through the turbine blade to conduct.
  • the invention further relates to a turbine, re insbesonde ⁇ a gas turbine, with at least one turbine stage comprehensively a plurality of turbine blades.
  • the object of the invention is a turbine blade having an internally cooled turbine blade, which Wenig ⁇ least one in the longitudinal direction of the turbine blade-bridging cooling air main channel Vietnamesere- configured to cool air from egg ⁇ nem arranged in a region of a turbine blade root cooling air passage inlet in the direction of a turbine blade tip through the turbine blade to conduct, solved, being inside the at least one cooling air main channel is arranged a hollow Leitein ⁇ direction for guiding cooling air, through which independently of the cooling air main channel cooling air can be introduced downstream of the cooling air main duct inlet into the turbine blade.
  • This guided through the hollow guide cooling air is introduced according to the invention, bypassing a significant heating by hot gas flowing around the turbine blade blade walls further back into the cooling air main channel.
  • the center part of the turbine blade can be cooled more effectively than before.
  • air main conduit means for conducting further cooling air are provided in the present case at least within the refrigerator, by means of which this additional cooling air can be indepen ⁇ dependent at least partially guided by an introduced through the cooling air duct inlet directly into the cooling air main channel cooling air through the cooling air main channels.
  • the effect can be obtained that can be cooled in the cooling air main channel has already been heated cooling air through the at ⁇ additional cooling air by at least a portion of the indwelling of the heated cooling air heat energy is transferred to the additional cooling air.
  • the total existing cooling air is cooler than without the hollow guide according to the invention. In this respect too ⁇ sharmaji cooling effect on the turbine blade is achieved.
  • the cooling air introduced directly into the cooling air main duct through the main cooling air inlet can cool the walls of the main cooling air duct directly behind the main air duct inlet, but this cooling air is already warmed up, the additional cooling air directed through the hollow duct is added to the already heated cooling air only further back an additional cooling effect can be achieved in ⁇ within the cooling air main channel or on the walls of the cooling air main channel.
  • the term "further back" in the sense of the invention describes a location within the cooling air main channel at which the additional cooling air is introduced into the cooling air main channel and which is preferably more than 30% or 40% of the total length of the cooling air main channel away from the main cooling air channel inlet ,
  • the hollow guide means different ⁇ Lich within the at least one cooling air main channel out ⁇ forms can be.
  • it comprises a tube element with a circular tube cross-section.
  • this tube member may also have any other shaped tube cross section, if appropriate.
  • the tube cross section may be oval, rectangular, triangular or the like.
  • the present turbine blade can also be traversed by several cooling air channels.
  • a hollow guide device can also be arranged in a plurality of cooling air channels or possibly also in all of the cooling air channels.
  • the turbine blade according to the invention is preferably a turbine blade of a gas turbine and has spe- essential a hot gas turbine, since this turbine respect show ⁇ feln are thermally most heavily loaded, so that it is precisely these turbine blades are developed particularly advantageous by the present hollow guide NEN kön-.
  • the hollow guiding means comprises a tubular member having a length which is less than 80% or less than 60% of the cooling air main channel length. This allows heating of the cooling air can be reduced overall in ⁇ nerrenz the cooling air main channel.
  • a particularly favorable additional cooling effect can be achieved when the hollow guiding means comprises a tubular member having a length which is at least 30% or 40%, preferably ⁇ example 50%, the cooling air main channel length.
  • the cooling air outlet from which the largest, if not the entire run in the hollow fin cooling air ⁇ quantity can escape, is located at said positions of the cooling air main channel.
  • Coolant main channel is arranged centrally within the coolant main channel.
  • the hollow guide device comprises a diffuser.
  • the diffuser By means of the diffuser it is possible in a structurally simple manner, the Strömungsge ⁇ speed of the additional cooling air into the cooling air main channel such to reduced prior to entry that the additional cooling air can intensively mix with the rest of the already heated in ⁇ nerrenz the cooling air main channel cooling air before the cooling air Whole leaves the main cooling duct. As a result, the cooling efficiency can be increased again.
  • this diffuser can be of different shape.
  • the diffuser can be provided structurally simple by a funnel-shaped outlet of the tubular element of the hollow guide device.
  • cooling air main channel Internal cross-sectional area of the cooling air main channel additionally tapers. In this way, the air flowing through the cooling air main channel re ⁇ gulär cooling air is accelerated to the level of the outlet of the hollow guide, whereby this may conveniently fluidize with the air flowing out of the diffuser additional cooling air. As a result, a further increase in the cooling efficiency is achieved.
  • the diffuser is arranged at the end of the hollow guide device facing the turbine nozzle, so that the flow velocity of the additional cooling air can be reliably reduced after leaving a diameter-limited tube element of the hollow guide device.
  • cooling air outlet openings are arranged in outer walls of the turbine blade leaf, which in the longitudinal extent of the cooling air main channel le ⁇ diglich before a diffuser of the hollow guide
  • the cooling-air main duct walls are completely closed and sealed.
  • cooling air outlet openings are realized by corresponding introduced in the outer walls outlet holes.
  • the cooling main air channel in which according to the invention, the hollow guide device is integrated can be suitably formed if the cooling air main channel of outer walls of the turbine blade and one or two within the Turbi ⁇ nenschaufelblatts disposed rib members is designed, the hollow guide binenschaufelfuß starting from a turbo in the Coolant main channel protrudes.
  • the object of the invention is also achieved by a turbine, in particular ⁇ a special gas turbine, with at least one turbine stage comprising a plurality of turbine blades, wherein comprising at least one turbine stage turbine blades according ei ⁇ nem of the preceding features.
  • An equipped with thermally relieved turbine blades turbine can be operated not only requires less maintenance, but it also possesses a higher Standfestig ⁇ ness.
  • Figure 1 schematically shows a first longitudinal cross-sectional view of a divisional applications ⁇ turbine airfoil having disposed within a cooling air passage main hollow guide means for directing additional cooling air into the turbine airfoil;
  • FIG. 2 is a schematic view of a further longitudinally sectioned partial view of the turbine blade according to FIG. 1 rotated by 90 ° relative to the partial view shown in FIG.
  • FIG. 3 schematically shows a cross-sectional view of the turbine blade of Figures 1 and 2 along the Thomasli ⁇ never AA; and FIG. 4 schematically shows another cross-sectional view of the turbine blade blade from FIGS. 1 to 3 along the section line BB.
  • the turbine blade each partially shown in Figures 1 to 4 show different views of a 1 H disclosegastur ⁇ bine 2 has an internally cooled turbine blade 3 having a hollow profile. 4
  • the hollow section 4 in this case encloses a cavity 5 of the door ⁇ binenschaufel 1 is substantially defined by a front side wall 6 of the turbine blade 3 as well as by a
  • Insofar 6 and 7 respectively represent the front and rear side wall which Au ⁇ .wandungen 10 of the turbine airfoil. 3
  • the front side wall 6 in this case forms the pressure side 11 and the rear side wall 7 accordingly the suction side 12 of the turbine blade 1, since the turbine blade 1 in the operation of the hot gas turbine 2 in the direction 13 by a hot gas 14 is ⁇ flows or flows around (see Figures 3 and 4).
  • Within the cavity 5 are located for subdivision of the hollow section 4 still three rib members 15, 16 and 17, wel ⁇ che in the longitudinal direction 18 of the turbine blade 1 and the turbine blade 3 are arranged to extend.
  • the cavity is divided into at least one cooling air main channel 19 and in three other cooling air ducts 20, 21 and 22 5 by means of the three Rippenele ⁇ elements 15, 16 and 17, each of which likewise run in the longitudinal direction 18 of the turbine blade.
  • cooling air 23 is discharged from a cooling air main passage inlet (not shown) disposed in a portion 24 of a turbine blade root (not shown) shown) in the direction 25 of a further outer region 26 of a turbine blade tip (not shown) passed through the turbine blade 3 to cool the turbine blade ⁇ 3 from the inside.
  • This cooling air 23 is therefore fed directly via the not shown cooling air main channel inlet to the cooling air main channel 19 so that this cooling air 23 flows through the entire cooling ⁇ main air channel 19 provided parts 27 (only exempla- driven numbered) of the cooling air 23 previously not already been in the Outside walls 10 introduced outlet holes 28 have flowed outwardly into the environment 29 of the turbine blade 3.
  • a hollow guide 35 arranged to conduct additional cooling air 36, through which additional cooling air may be downstream initiated 36 behind thede povertymaschineka ⁇ naleinlass in the turbine blade 3, independently from the cooling air main channel nineteenth
  • the hollow guide 35 has a tubular element 38, which thus has a larger diameter at its end 39 facing the turbine blade tip.
  • the end 39 is in this case designed as a diffuser 40, so that the flow rate of the additional through the tubular element 38 Gelei ⁇ ended cooling air 36 is reduced in the main cooling air duct 19 before introduction. In this respect, more time for a more intensive mixing with the already heated
  • Cooling air 23 are provided. In this way, on the one hand, the already heated cooling air 23 and on the other hand, in particular the outer walls 10 of the additional
  • Cooling air 23 can flow, the cooling air main channel 19 to ei ⁇ nen is narrowed by the circular tube member 38.
  • this inner cross section is again tapered by the trich ⁇ terförmigen outlet 37, whereby the flowing in the cooling air ⁇ main channel 19 cooling air 23 is accelerated before it mixes with the additional cooling air 36.
  • the hollow guide device 35 is arranged approximately centrally in the cooling-air main channel 19 in order to allow the cooling air 23 within the cooling-air main channel 19 to flow as uniformly as possible.
  • the turbine blade 3 is cut at the level downstream of the diffuser 40, facing the flow direction 30 onto the hollow guide 35.
  • turbine blade 3 is cut according to the illustration of Figure 4 at the height of the tube member 38 with viewing direction opposite to the flow direction 30.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aube de turbine (1) comprenant une pale à refroidissement interne (3), qui forme au moins un canal principal d'air de refroidissement (19) s'étendant dans la direction longitudinale (18) de l'aube de turbine (1) pour diriger l'air de refroidissement (23) depuis une entrée de canal principal d'air de refroidissement, disposée dans une zone (24) d'une base d'aube de turbine, en direction (25) d'une extrémité d'aube de turbine à travers l'aube de turbine (3), un moyen de guidage creux (3) étant disposé à l'intérieur de l'au moins un canal principal d'air de refroidissement (19) pour guider de l'air de refroidissement supplémentaire (36), lequel moyen de guidage creux est traversé par de l'air de refroidissement supplémentaire (36) qui peut être introduit en aval dans la pale d'aube de turbine (3) en arrière de l'entrée de canal principal d'air de refroidissement indépendamment du canal principal d'air de refroidissement (19).
EP15725320.4A 2014-06-17 2015-05-27 Aube de turbine et turbine Not-in-force EP3134621B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14172768.5A EP2957724A1 (fr) 2014-06-17 2014-06-17 Aube de turbine et turbine
PCT/EP2015/061658 WO2015193068A1 (fr) 2014-06-17 2015-05-27 Aube de turbine et turbine

Publications (2)

Publication Number Publication Date
EP3134621A1 true EP3134621A1 (fr) 2017-03-01
EP3134621B1 EP3134621B1 (fr) 2018-12-26

Family

ID=50943194

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14172768.5A Withdrawn EP2957724A1 (fr) 2014-06-17 2014-06-17 Aube de turbine et turbine
EP15725320.4A Not-in-force EP3134621B1 (fr) 2014-06-17 2015-05-27 Aube de turbine et turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP14172768.5A Withdrawn EP2957724A1 (fr) 2014-06-17 2014-06-17 Aube de turbine et turbine

Country Status (2)

Country Link
EP (2) EP2957724A1 (fr)
WO (1) WO2015193068A1 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1204021B (de) * 1959-04-27 1965-10-28 Rolls Royce Schaufel fuer Axialstroemungsmaschinen, insbesondere Gasturbinen
US3867068A (en) * 1973-03-30 1975-02-18 Gen Electric Turbomachinery blade cooling insert retainers
GB1605194A (en) * 1974-10-17 1983-04-07 Rolls Royce Rotor blade for gas turbine engines
US3994622A (en) * 1975-11-24 1976-11-30 United Technologies Corporation Coolable turbine blade
DE3603350A1 (de) * 1986-02-04 1987-08-06 Walter Prof Dipl Ph Sibbertsen Verfahren zur kuehlung thermisch belasteter bauelemente von stroemungsmaschinen, vorrichtung zur durchfuehrung des verfahrens sowie ausbildung thermisch belasteter schaufeln

Also Published As

Publication number Publication date
WO2015193068A1 (fr) 2015-12-23
EP2957724A1 (fr) 2015-12-23
EP3134621B1 (fr) 2018-12-26

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