EP2957724A1 - Aube de turbine et turbine - Google Patents

Aube de turbine et turbine Download PDF

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Publication number
EP2957724A1
EP2957724A1 EP14172768.5A EP14172768A EP2957724A1 EP 2957724 A1 EP2957724 A1 EP 2957724A1 EP 14172768 A EP14172768 A EP 14172768A EP 2957724 A1 EP2957724 A1 EP 2957724A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
turbine blade
turbine
hollow guide
main channel
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Withdrawn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
EP14172768.5A
Other languages
German (de)
English (en)
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
Siemens Corp
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
Priority to EP14172768.5A priority Critical patent/EP2957724A1/fr
Priority to EP15725320.4A priority patent/EP3134621B1/fr
Priority to PCT/EP2015/061658 priority patent/WO2015193068A1/fr
Publication of EP2957724A1 publication Critical patent/EP2957724A1/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Withdrawn legal-status Critical Current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
    • F01D5/12—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

  • the invention relates to a turbine blade having an internally cooled turbine blade, which at least one configured in the longitudinal direction of the turbine blade cooling air main channel configured to direct cooling air from a arranged in a region of a turbine blade root cooling air duct inlet in the direction of a turbine blade tip through the turbine blade.
  • the invention further relates to a turbine, in particular a gas turbine, with at least one turbine stage comprising a plurality of turbine blades.
  • turbine blades and turbines and gas turbines are already known from the prior art.
  • the turbine blades are flowed around by hot gas, which in particular heats the turbine blades and thus sometimes subjected to high thermal stress.
  • turbine blades in this regard are often internally cooled. That is, cooling air passages are provided in the turbine airfoils through which cooling air flows to counteract critical heating of the turbine airfoils. The disadvantage here is that this cooling air heats itself on the way through the turbine blades to the heated turbine blade outer walls.
  • the object of the invention is achieved by a turbine blade with an internally cooled turbine blade, which at least one extending in the longitudinal direction of the turbine blade cooling air main channel to direct cooling air from a arranged in a region of a turbine blade root cooling air duct inlet in the direction of a turbine blade tip through the turbine blade, within at least one cooling air main passage is provided with a hollow guide for guiding cooling air through which cooling air downstream of the cooling air main passage inlet into the turbine bucket blade can be introduced independently of the cooling air main passage.
  • 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.
  • means are thus provided for conducting further cooling air, by means of which this additional cooling air is independent from a cooling air introduced directly into the cooling air main passage through the cooling air passage inlet, at least partially through the cooling air main passage.
  • the effect can be obtained that the cooling air already heated in the cooling air main passage can be cooled by the additional cooling air by transmitting at least a part of the heat energy inherent to the heated cooling air to the additional cooling air.
  • the total existing cooling air is cooler than without the hollow guide according to the invention. As such, an additional cooling effect is achieved on the turbine bucket blade.
  • 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 spaced from the cooling air main channel inlet.
  • the additional cooling air conducted through the hollow guide means may flow at a flow velocity inside the main cooling air passage which is different from a flow velocity of a cooling air led directly from the cooling air main passage to promote mixing in merging the cooling air.
  • hollow guide device can be designed differently within the at least one cooling air main channel.
  • this tube member 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 especially of a hot gas turbine, since relevant turbine blades are subject to particularly high thermal loads, so that it is precisely these turbine blades that can be developed particularly advantageously by the present hollow guide.
  • the hollow baffle comprises a tubular element having a length that is less than 80% or less than 60% of the main air channel length. As a result, heating of the cooling air as a whole can be reduced within the cooling air main channel.
  • the hollow guide comprises a tube member having a length which is at least 30% or 40%, preferably 50%, of the main length of the cooling air channel.
  • the cooling air outlet from which the largest, if not the entire, amount of cooling air guided in the hollow baffle can exit, is located at said positions of the main cooling air duct.
  • the hollow guide device has a cooling air outlet which widens conically in the flow direction, it is possible for the additional cooling air introduced through the hollow guide device in the rear of the cooling air main channel to distribute itself more favorably over the cross section of the cooling air main channel after this additional cooling air has flowed into the cooling air main channel. As a result, the cooling efficiency can be further increased.
  • the hollow guide device comprises a diffuser.
  • the diffuser it is possible in a structurally simple manner to reduce the flow velocity of the additional cooling air prior to entry into the cooling air main channel in such a way that the additional cooling air can mix more intensively with the remaining cooling air already heated within the main cooling air channel before the cooling air as a whole leaves the main cooling air channel , 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.
  • a diffuser of the hollow guide means additionally tapers the inner cross-sectional area of the cooling air main channel.
  • the diffuser is disposed at the turbine blade tip end of the hollow guide, so that the flow velocity of the additional cooling air after leaving a diameter-limited tube member of the hollow guide can be reliably reduced.
  • cooling air outlet openings are arranged in outer walls of the turbine blade leaf, which are arranged in the longitudinal extension of the cooling air main channel only in front of a diffuser of the hollow guide and / or only after this diffuser. If no cooling air outlet openings are provided at the level of the diffuser, the risk can be reduced that an excessive proportion of cooling air flows out of the cooling air outlet openings due to an increase in pressure due to the accelerated cooling air.
  • the cooling-air main duct walls are completely closed and sealed.
  • the longitudinal extension of the cooling air main channel in the present case is aligned with the longitudinal direction of the turbine blade or of the turbine blade leaf.
  • cooling air outlet openings are realized by corresponding introduced in the outer walls outlet holes.
  • the cooling air main channel in which the hollow guide device according to the invention is integrated, may be expediently designed when the cooling air main channel is configured by outer walls of the turbine blade leaf and one or two rib elements arranged inside the turbine blade leaf, wherein the hollow guide device projects from a turbine blade root into the cooling air main channel.
  • the object of the invention is also achieved by a turbine, in particular a gas turbine, having at least one turbine stage comprising a multiplicity of turbine blades, wherein the at least one turbine stage comprises turbine blades according to one of the preceding features.
  • a turbine equipped with thermally relieved turbine blades can not only be operated with less maintenance, but also has a higher stability.
  • Turbine blade 1 of a hot gas turbine 2 partially shown in different views has an internally cooled turbine blade 3 with a hollow profile 4.
  • the hollow profile 4 in this case encloses a cavity 5 of the turbine blade 1 substantially through a front side wall 6 of the turbine blade 3 and through a rear side wall 7 of the turbine blade 3, which merge into each other both at the leading edge 8 of the turbine blade 3 and at its trailing edge 9.
  • the front and rear side walls 6 and 7 embody the outer walls 10 of the turbine blade 3, respectively.
  • 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 is flowed through or flows around a hot gas 14 (see FIGS. 3 and 4 ).
  • the cavity 5 is subdivided into at least one cooling air main channel 19 and three further cooling air channels 20, 21 and 22, which likewise extend in the longitudinal direction 18 of the turbine blade 1.
  • cooling air 23 is directed from a central cooling duct inlet (not shown) in direction 25 of a further outboard portion 26 of a turbine blade tip (not shown) through the turbine blade 3 to the turbine blade 3 to cool from the inside.
  • This cooling air 23 is thus fed directly into the cooling air main duct 19 via the cooling air main duct inlet, not shown here, so that this cooling air 23 flows through the entire cooling air main duct 19, provided parts 27 (only exemplified) of the cooling air 23 have not previously been discharged through outlet bores introduced into the outer walls 10 28 are discharged to the outside in the environment 29 of the turbine blade 3.
  • the cooling air 23 introduced by means of the cooling air main channel inlet heats up more and more, since starting from the heated outer walls 10 a heat transfer to heat energy to the cooling air 23 takes place.
  • a hollow guide 35 for conducting additional cooling air 36 inside the cooling air main channel 19 there is arranged a hollow guide 35 for conducting additional cooling air 36, through which additional cooling air 36 downstream of the cooling air main channel inlet into the turbine blade 3 can be introduced independently of the cooling air main channel 19.
  • a funnel-shaped outlet 37 of the hollow nozzle 35 - extending from the main cooling-air duct inlet - lies approximately at 50% of the length of the main cooling-air channel 19, so that approximately halfway the cooling air main channel 19 again additional cooling air 36 can be introduced into this cooling air main channel 19.
  • 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 designed as a diffuser 40, so that the flow velocity of the additional cooling air 36 conducted through the pipe element 38 is reduced before it is introduced into the cooling-air main duct 19.
  • more time for a more intensive mixing with the already heated cooling air 23 can be made available.
  • the already heated cooling air 23 and, on the other hand, in particular the outer walls 10 can be cooled more favorably by 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 height downstream of the diffuser 40, viewed in the direction opposite to the flow direction 30 on the hollow guide 35th
  • turbine blade 3 according to the illustration of FIG. 4 cut at the height of the tube member 38 facing the direction of flow 30.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14172768.5A 2014-06-17 2014-06-17 Aube de turbine et turbine Withdrawn EP2957724A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP14172768.5A EP2957724A1 (fr) 2014-06-17 2014-06-17 Aube de turbine et turbine
EP15725320.4A EP3134621B1 (fr) 2014-06-17 2015-05-27 Aube de turbine et turbine
PCT/EP2015/061658 WO2015193068A1 (fr) 2014-06-17 2015-05-27 Aube de turbine et turbine

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2957724A1 true EP2957724A1 (fr) 2015-12-23

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 After (1)

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

Country Status (2)

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

Citations (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
US3994622A (en) * 1975-11-24 1976-11-30 United Technologies Corporation Coolable turbine blade
GB1605194A (en) * 1974-10-17 1983-04-07 Rolls Royce Rotor blade for gas turbine engines
EP0232782A1 (fr) * 1986-02-04 1987-08-19 MAR-RESEARCH Gesellschaft für Forschung und Entwicklung mbH Méthode et dispositif de refroidissement des aubes de turbines thermiques

Patent Citations (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
EP0232782A1 (fr) * 1986-02-04 1987-08-19 MAR-RESEARCH Gesellschaft für Forschung und Entwicklung mbH Méthode et dispositif de refroidissement des aubes de turbines thermiques

Also Published As

Publication number Publication date
EP3134621A1 (fr) 2017-03-01
WO2015193068A1 (fr) 2015-12-23
EP3134621B1 (fr) 2018-12-26

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