EP1266127A1 - Systeme de refroidissement pour aube de turbine - Google Patents

Systeme de refroidissement pour aube de turbine

Info

Publication number
EP1266127A1
EP1266127A1 EP01919384A EP01919384A EP1266127A1 EP 1266127 A1 EP1266127 A1 EP 1266127A1 EP 01919384 A EP01919384 A EP 01919384A EP 01919384 A EP01919384 A EP 01919384A EP 1266127 A1 EP1266127 A1 EP 1266127A1
Authority
EP
European Patent Office
Prior art keywords
insert
blade
horizontal ribs
wall
cooling fluid
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
EP01919384A
Other languages
German (de)
English (en)
Other versions
EP1266127B1 (fr
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 EP01919384A priority Critical patent/EP1266127B1/fr
Publication of EP1266127A1 publication Critical patent/EP1266127A1/fr
Application granted granted Critical
Publication of EP1266127B1 publication Critical patent/EP1266127B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a blade, in particular a turbine blade, with at least one channel which is delimited by walls, wherein an insert which can be acted upon by a cooling fluid is inserted into at least one channel.
  • Chambers are formed between the insert and the walls of the blade, which run in the direction of a longitudinal axis of the blade.
  • the cooling fluid enters the chamber from the insert and impacts the walls of the blade. It then flows along the walls and exits through specially designed chambers on the outside of the walls and from there the surroundings.
  • the effect of convection cooling when the cooling fluid flows along the walls is only slight, since the flow length is very limited. Mixing of the cooling fluid also occurs in the chambers along the longitudinal axis of the blade, so that targeted cooling is not possible.
  • Blades with partially hollow walls through which a cooling fluid flows. Due to the reduction in the wall thickness in the area of the hollow chambers, a high cooling efficiency is achieved. However, blades with such hollow walls require a complicated casting process with high reject rates and are therefore very expensive.
  • the object of the present invention is therefore to provide a blade which, with simple manufacture, achieves an improvement in the cooling effect.
  • this object is achieved in a shovel of the type mentioned in the introduction in that at least one of the walls is provided with a number of horizontal ribs which are arranged between the insert and the wall, and in that the insert is provided with openings through which the
  • Cooling fluid from the insert can enter between the horizontal ribs.
  • the horizontal ribs guide the coolant along the wall of the blade and prevent the coolant from flowing
  • the insert touches the horizontal ribs.
  • the insert is clipped and aligned in the desired position.
  • the horizontal ribs, the insert and the wall form the chambers through which the cooling fluid flows.
  • the chambers reliably prevent the cooling fluid from flowing in the direction of the longitudinal axis of the blade.
  • the cooling effect along the longitudinal axis of the blade can be varied in a targeted manner by applying the cooling fluid to the chambers differently.
  • the openings of the insert are at a first end of the chambers and exit openings for the cooling fluid m the wall are arranged at a second end of the chambers.
  • the cooling fluid therefore flows along the entire length of the chamber along the wall to be cooled, so that the convection cooling is further improved.
  • the horizontal ribs can be arranged essentially perpendicular to the longitudinal axis of the blade.
  • an angular position can be provided. With a vertical arrangement with respect to the longitudinal axis, the length of the horizontal ribs and thus the chambers is minimized. The angular position enables the length of the chambers to be increased and thus further improved convection cooling.
  • the insert is advantageously closed at one end.
  • the cooling fluid is only supplied from the other end of the insert.
  • the cooling fluid is prevented from escaping through the end facing away from the supply side, so that the cooling efficiency is increased.
  • cooling fluid can be supplied from both ends.
  • the turbulators serve to stiffen the wall and merge into one another and m the horizontal ribs. This results in a significant increase in rigidity without additional material. With the same strength of the blade, the wall thickness can be reduced again. At the same time, good heat exchange between the walls and the cooling fluid is achieved. This results in high cow efficiency and high overall efficiency.
  • the stiffening of the wall does not only occur in the area of a single turbulator. Rather, a large-area stiffening is provided by connecting the turbulators to one another.
  • the turbulators are advantageously straight. The use of straight turbulators enables high rigidity with simple manufacture.
  • the turbulators are arranged such that, together with the horizontal ribs, they form mutually adjacent recesses in the form of polygons, in particular triangles or rhombuses.
  • the inside of the wall is provided with a honeycomb structure.
  • the individual polygons or honeycombs each form a closed, highly resilient cross-section and support each other. A substantial increase in rigidity can be achieved.
  • the wall thickness of the wall is reduced at least in the area between the turbulators. This reduction in wall thickness is made possible by the fact that the turbulators stiffen the wall. By reducing the wall thickness, the cow's efficiency is increased again.
  • the turbulators can advantageously be used as metal feed channels when casting the blade. The honeycomb structure is therefore easy to manufacture.
  • the blade according to the invention can be designed as a guide blade or as a rotor blade of a rotary machine.
  • FIG. 1 shows a longitudinal section through a rotary machine
  • FIG. 2 shows a perspective, broken-away representation of a blade
  • 3 shows a plan view of the inside of a wall of the blade
  • FIG. 8 shows a view similar to FIG. 7 in the second embodiment.
  • FIG. 1 shows a longitudinal section through a rotary machine in the form of a turbine 10 with a housing 11 and a rotor 12.
  • the housing 11 is provided with guide vanes 13 and the rotor 12 with rotor blades 14.
  • the turbine 10 is flowed through according to arrow 15 by a fluid which flows along the guide vanes 13 and rotor blades 14 and rotates the rotor 12 m around an axis 16.
  • the temperature of the fluid is relatively high in many application cases, particularly in the area of the first row of blades (shown on the left in FIG. 1). A cooling of the guide vanes 13 and blades 14 is therefore provided.
  • Flow of the cooling fluid is indicated schematically by the arrows 17, 18.
  • FIG. 2 schematically shows a broken view of a guide vane 13.
  • the guide vane 13 has curved outer walls 19, 20.
  • the interior lying between the outer walls 19, 20 is divided into a total of three channels 22 via two partition walls 21 m.
  • An insert 25 is inserted into each of the channels 22.
  • the embedding of the middle channel 22 is not shown for better illustration.
  • the two outer walls 19, 20 are provided with a number of horizontal ribs 24 in each of the channels 22.
  • the horizontal ribs 24 run along the walls 19, 20 and extend as far as the partition walls 21.
  • Turbulators 23 are arranged between the horizontal ribs 24.
  • the inserts 25 touch the horizontal ribs 24.
  • the cooling fluid in particular cooling air, is supplied to an interior 26 of the inserts 25.
  • the inserts 25 are provided with a number of openings 27 through which the cooling fluid exits the space between the outer walls 19, 20 and the insert 25.
  • the cooling fluid then flows along the outer walls 19, 20 to outlet openings 28 in the walls 19, 20. This flow is indicated schematically by the arrow 30.
  • the openings 27 of the inserts 25 are arranged at a distance from the opening 28 of the outer walls 19, 20. In the exemplary embodiment shown, the opening openings 28 form essentially straight rows 29.
  • the cooling fluid emerging from the inserts 25 first impacts the outer walls 19, 20 and leads there to one
  • the front edge of the guide vane 13 shown on the left in FIG. 2 is additionally provided with direct impact cooling.
  • the insert 25 has further openings 36 for this impingement cooling, which are arranged directly behind the front edge of the guide vane 13.
  • the cooling medium exits directly through these openings 36 and provides targeted cooling of the front edge of the guide vane 13.
  • the associated insert 25 is also provided with a further opening 37 in the region of the rear edge of the guide vane 13. Through this opening 37, cooling fluid emerges directly in a narrow gap 38 between the outer walls 19, 20 and causes film cooling there.
  • FIGS. 3 to 5 show further details of the inside of the outer wall 19.
  • the horizontal ribs 24 run essentially at right angles to a longitudinal axis 31 of the guide vane 13. They are arranged parallel to one another. Between the horizontal ribs 24 straight turbulators 23 are arranged, which merge into one another and the ho ⁇ zonal ⁇ ppen 24.
  • the front edge 33 of the horizontal ribs 24 merges into the partition 21 in the middle channel 22 m. In the channel 22 on the left in FIG. 2, the front edge 33 is arranged at some distance from the foremost outflow openings 28.
  • the cooling fluid enters this chamber 32 through the openings 27 of the insert 25 m. It then flows according to arrow 30 to the opening 28.
  • the openings 27 are arranged at one end of the chamber 32 and the opening 28 at the other end. This maximizes the distance that the cooling fluid traverses as it flows along the outer wall 19. This results in maximum convection cooling.
  • the effect of convection cooling is further enhanced by the turbulators 23, since these improve the heat exchange between the outer wall 19 and the cooling fluid.
  • the chambers 32 can be supplied with the cooling fluid in different ways. This is achieved by varying the number and / or the size of the openings 27 in the insert 25. In this way, individual chambers 32 can be specifically cooled more or less than others. The cooling can thus be specifically adjusted along the longitudinal axis 31 of the guide vane 13 and adapted to the prevailing boundary conditions.
  • the turbulators 23 also serve to stiffen the outer wall 19.
  • the straight turbulators 23 are arranged in such a way that they form polygons. In FIG. 3, game triangles and shown in Figure 6 as examples diamonds.
  • the stiffening achieved by the turbulators 23 enables a reduction in the wall thickness d of the outer wall 19 in the region between the turbulators 23. Because of this reduction in the wall thickness d, the cooling efficiency increases further.
  • Figure 6 shows a plan view of the inside of the outer wall 19 m of the second embodiment.
  • the turbulators 24 are opposite to the longitudinal axis 31
  • turbulators 23 are provided, four of which are combined to form a rhombus. The reduction in the wall thickness is indicated schematically in these diamonds with visible edges.
  • the second outer wall 20 is also provided with corresponding turbulators 23 and horizontal ribs 24.
  • the horizontal ribs 24 and turbulators 23 can alternatively or additionally also be provided for a moving blade 14.
  • FIGS. 7 and 8 show two configurations of an insert 25. In the configuration according to FIG.
  • Cooling fluid is supplied from both ends 34, 35 of the insert and exits through openings 27.
  • Such an insert 25 can be used, for example, in the first row of blades.
  • an insert 25 according to FIG. 8 can be provided, which is closed at the end 34.
  • the cooling fluid is then only supplied via the end 35.
  • This insert 25 is used in the further rows of blades, in which only one end of the guide vane 13 or the rotor blade 14 can be acted upon by the cooling fluid via the housing 11 or the rotor 12. Due to the horizontal ribs 24 provided according to the invention, there is a directed flow of the cooling fluid along the outer walls 19, 20. The cooling effect is therefore significantly improved. At the same time, simple manufacture is possible since there is no need for blades with hollow walls.

Abstract

L'invention concerne une aube (13 ; 14) pour une turbine (10), comportant au moins un canal (22) délimité par les parois (19, 20, 21). Une pièce d'insertion (25) alimentée par un fluide de refroidissement est introduite dans au moins un canal (22). L'invention est caractérisée en ce qu'au moins l'une des parois (19 ; 20) est munie d'une pluralité de nervures horizontales (24) disposées entre la pièce d'insertion (25) et la paroi (19 ; 20), et en ce que la pièce d'insertion (25) est munie d'orifices (27) à travers lesquels le fluide de refroidissement sortant de la pièce (25) peut pénétrer entre les nervures horizontales (24). Le fluide de refroidissement circule ainsi le long de la paroi (19, 20) et est guidé par les nervures horizontales, ce qui permet d'obtenir un refroidissement par convection amélioré.
EP01919384A 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine Expired - Lifetime EP1266127B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01919384A EP1266127B1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00106245 2000-03-22
EP00106245A EP1136651A1 (fr) 2000-03-22 2000-03-22 Système de refroidissement pour une aube de turbine à gaz
PCT/EP2001/002755 WO2001071163A1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine
EP01919384A EP1266127B1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine

Publications (2)

Publication Number Publication Date
EP1266127A1 true EP1266127A1 (fr) 2002-12-18
EP1266127B1 EP1266127B1 (fr) 2005-01-12

Family

ID=8168201

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00106245A Withdrawn EP1136651A1 (fr) 2000-03-22 2000-03-22 Système de refroidissement pour une aube de turbine à gaz
EP01919384A Expired - Lifetime EP1266127B1 (fr) 2000-03-22 2001-03-12 Systeme de refroidissement pour aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP00106245A Withdrawn EP1136651A1 (fr) 2000-03-22 2000-03-22 Système de refroidissement pour une aube de turbine à gaz

Country Status (6)

Country Link
US (1) US6769875B2 (fr)
EP (2) EP1136651A1 (fr)
JP (1) JP4637437B2 (fr)
CN (1) CN1293285C (fr)
DE (1) DE50105062D1 (fr)
WO (1) WO2001071163A1 (fr)

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Also Published As

Publication number Publication date
JP2003528246A (ja) 2003-09-24
CN1418284A (zh) 2003-05-14
US20030049127A1 (en) 2003-03-13
DE50105062D1 (de) 2005-02-17
WO2001071163A1 (fr) 2001-09-27
EP1266127B1 (fr) 2005-01-12
CN1293285C (zh) 2007-01-03
EP1136651A1 (fr) 2001-09-26
JP4637437B2 (ja) 2011-02-23
US6769875B2 (en) 2004-08-03

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