WO2001055559A1 - Aube de turbine poreuse et turbine equipee de telles aubes - Google Patents

Aube de turbine poreuse et turbine equipee de telles aubes Download PDF

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Publication number
WO2001055559A1
WO2001055559A1 PCT/EP2001/000239 EP0100239W WO0155559A1 WO 2001055559 A1 WO2001055559 A1 WO 2001055559A1 EP 0100239 W EP0100239 W EP 0100239W WO 0155559 A1 WO0155559 A1 WO 0155559A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
blades
blade
microholes
steam
Prior art date
Application number
PCT/EP2001/000239
Other languages
German (de)
English (en)
Inventor
Christoph NÖLSCHER
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2001055559A1 publication Critical patent/WO2001055559A1/fr

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Definitions

  • the invention relates to a turbine, in particular to a gas or steam turbine, with guide vanes arranged in a turbine housing and with rotor blades fastened to a turbine shaft.
  • the working means for the gas turbine is obtained by burning a fuel, e.g. Petroleum or natural gas, produced by supplying compressed air, whereby the working fluid temperature is currently around 1200 ° C to 1400 ° C.
  • a fuel e.g. Petroleum or natural gas
  • steam turbines previously used can achieve a system efficiency of approx. 38% to 40% at a live steam temperature of approx. 540 ° C.
  • a live steam temperature of approx. 540 ° C.
  • its turbine shaft and in particular the blade roots of rotor blades can be cooled by means of cooling steam.
  • the invention is based on the object of constructively developing a turbine, in particular a gas or steam turbine, in such a way that its efficiency is increased.
  • This object is achieved according to the invention by the features of claim 1.
  • at least some of the guide and / or rotor blades of the turbine are provided with a large number of microholes.
  • the invention is based on the knowledge that the efficiency of both a gas turbine and a steam turbine is limited in particular by the fact that the flow of the working medium along the blade surface is not always ideally laminar. In particular in the boundary layer near the surface, vortices and thus a turbulent flow of the working medium form, which lead to a conversion of the kinetic energy of the working medium into heat. A not inconsiderable proportion of flow losses occurring in such a turbine can be attributed to this effect.
  • the invention is based on the consideration that such eddies or turbulent flows on the blade surface can be avoided or at least reduced if a part of the working medium is suctioned off at the boundary layer near the surface and a laminar flow of the working medium is thereby practically forced on the blade surface , With this measure, the efficiency of the turbine can be increased by a few percentage points.
  • both the guide blades provided with microholes and the rotor blades provided with microholes are hollow. Part of the working medium flowing past the blade surface is thus sucked away from the blade surface into the interior of the hollow blade.
  • the guide vanes are expediently connected to an outer suction channel, preferably provided in or on the turbine housing, while the interior of the hollow rotor blades is connected to the interior of a hollow turbine shaft.
  • the vacuum required for suction is advantageously generated by the fact that the microholes are connected to a turbine part, which has a relatively low working fluid pressure flowing around it. A pressure drop required for this is already present due to the expansion of the working fluid in the turbine between the turbine inlet and the turbine outlet and is therefore available for extraction.
  • the microholes are designed as through-holes which enter the turbine blade on the surface side facing the working fluid flow and exit on the opposite rear side of the blade.
  • the pressure drop between the front and rear of the turbine blade is used for the suction.
  • the necessary suction of work fluid flowing along the respective turbine blade is preferably generated in that the microholes have a connection to a turbine part which is surrounded by work fluid of comparatively low pressure. An additional unit for suction can thus be saved. Exemplary embodiments of the invention are explained in more detail below with reference to a drawing. In it show:
  • FIG. 1 shows a hollow turbine blade provided with microholes
  • FIG. 2 schematically shows a turbine provided with a number of such turbine blades with an outer suction duct and with a hollow turbine shaft
  • FIG. 3 shows a steam-cooled steam turbine with turbine blades provided with through-holes in a representation according to FIG.
  • the turbine blade 1 shown in FIG. 1 with a blade leaf 2 curved like a banana and a blade root 3 like a hammer head is hollow.
  • the interior 4 of the airfoil 2 and the interior 5 of the blade root 3 are connected to one another.
  • the turbine blade 1 is provided in the region of the airfoil 2 with a large number of microholes 6 which enter the blade surface 7 and open into the interior 4.
  • a portion ⁇ I M of the working medium or working medium M flowing along its blade surface 7 is sucked off via the microholes in the direction of arrow 8 into the interior 4 of the turbine blade 1 and flows out in the direction of arrow 9 via the interior 5 of the blade root 3 the turbine blade 1.
  • a number of such turbine blades 1, which are provided with microholes 6, are used as guide blades 1 a and as blades 1 b.
  • the guide vanes la are in a manner not shown on the respective blade root 3 in Turbine housing 11 anchored, while the blades lb are attached to a hollow turbine shaft 12.
  • the inner spaces 4, 5 of the guide vanes 1 a are connected to a suction duct 13 provided in the outer region of the turbine housing 11.
  • the inner spaces 4, 5 of the rotor blades 1b are connected to a cavity 14 of the turbine shaft 12, which cavity also serves as a suction channel.
  • the portion m M of the working medium M flowing through the micro-holes 6 of the guide vanes la m through the discharge channel 13 is preferably fed back to the turbine 10 and introduced into its working space 15.
  • the suction channel 13 is connected via a number of openings 16 to the working space 15 at a point at which the pressure pi of the working medium M is less than the pressure p 2 of the working medium M in the region of its entry via the microholes 6 in the corresponding guide vanes la.
  • the extraction of the portion m M of the working medium M via the micro-holes 6 of the rotor blades 1b is carried out analogously, in that this portion m M of the working medium M is introduced through the corresponding guide blades 1b and through the turbine shaft 14 at a corresponding point m into the working space 15 of the turbine 10.
  • the turbine shaft 14 also has corresponding openings 17 in the region of comparatively low medium pressure pi.
  • FIG 3 shows a steam turbine 10 which is cooled by means of cow steam KD and which is fed fresh steam FD on the inlet side with a steam steam temperature T FD of, for example, 600 ° C. to 1000 ° C.
  • T FD fresh steam temperature
  • the hollow guide vanes la are supplied on the one hand via the turbine housing 11 and on the other hand via the hollow turbine shaft 14 the rotor blades 14b of the cow steam KD.
  • the cooling steam KD flowing through the turbine blades la, lb enters the working space 15 of the turbine through corresponding openings in the turbine blades la, lb Steam turbine 10 ⁇ out and mixes there with the live steam FD relaxing along the rows of blades. This leaves the turbine 10 as exhaust steam AD.
  • the steam-cooled turbine blades la, lb are followed in the flow direction 18 of the live steam FD along the turbine shaft 14 by further rows of blades with guide and rotor blades la and lb, which in turn are provided with microholes 6.
  • the micro-holes are advantageously carried out at this expedient From guide die in the form of through holes 6 ⁇ , which pass through the turbine blades la lb.
  • the passage of a portion ⁇ I of live steam FD through these through holes 6 ⁇ is due to the pressure difference between the steam pressure p 2 on the inflow side of the corresponding turbine blades la, lb and the pressure on the outflow or rear side of the corresponding turbine blade la, lb pi forced.
  • the size of the micro-holes 6, 6 x is suitably in the u - region, wherein the inner diameter d of the micro holes is 6.6, for example 0.05 mm.
  • the distance a between adjacent microholes 6, 6 is expediently less than 1 mm.
  • the number of microholes 6, 6 provided on the respective blade surface 7 is in the order of 10 2 to 10 5, depending on the size of the respective airfoil 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention vise à réduire la formation de turbulences sur les surfaces d'aubes (7) d'une turbine (10, 10'), notamment d'une turbine à gaz ou à vapeur. A cet effet, des aubes directrices (1a) disposées dans une enveloppe de turbine (11) ou des aubes mobiles (1b) fixées sur un arbre de turbine (12) sont équipées d'une multitude de micro-orifices (6, 6') afin d'aspirer la couche limite au moyen d'un gradient de pression.
PCT/EP2001/000239 2000-01-27 2001-01-10 Aube de turbine poreuse et turbine equipee de telles aubes WO2001055559A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP00101581 2000-01-27
EP00101581.7 2000-01-27

Publications (1)

Publication Number Publication Date
WO2001055559A1 true WO2001055559A1 (fr) 2001-08-02

Family

ID=8167707

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2001/000239 WO2001055559A1 (fr) 2000-01-27 2001-01-10 Aube de turbine poreuse et turbine equipee de telles aubes

Country Status (1)

Country Link
WO (1) WO2001055559A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2900692A1 (fr) * 2006-05-05 2007-11-09 Snecma Sa Pale de compresseur comprenant un dispositif d'aspiration
US8336315B2 (en) 2004-02-18 2012-12-25 Siemens Aktiengesellschaft Gas turbine with a compressor housing which is protected against cooling down and method for operating a gas turbine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2597510A (en) * 1947-04-15 1952-05-20 Worthington Pump & Mach Corp Blade element for rotary fluid machines
GB1085227A (en) * 1963-07-26 1967-09-27 Rolls Royce Improvements in or relating to gas turbine engines
US3656863A (en) * 1970-07-27 1972-04-18 Curtiss Wright Corp Transpiration cooled turbine rotor blade
GB1532815A (en) * 1976-09-27 1978-11-22 Rolls Royce Rotor blades for ducted fans
JPS5688902A (en) * 1979-12-19 1981-07-18 Toshiba Corp Turbine blade
US5480284A (en) * 1993-12-20 1996-01-02 General Electric Company Self bleeding rotor blade
EP0726384A1 (fr) * 1995-02-13 1996-08-14 Abb Research Ltd. Aube statorique pour turbines à vapeur
US5803410A (en) * 1995-12-01 1998-09-08 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Skin friction reduction by micro-blowing technique

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2597510A (en) * 1947-04-15 1952-05-20 Worthington Pump & Mach Corp Blade element for rotary fluid machines
GB1085227A (en) * 1963-07-26 1967-09-27 Rolls Royce Improvements in or relating to gas turbine engines
US3656863A (en) * 1970-07-27 1972-04-18 Curtiss Wright Corp Transpiration cooled turbine rotor blade
GB1532815A (en) * 1976-09-27 1978-11-22 Rolls Royce Rotor blades for ducted fans
JPS5688902A (en) * 1979-12-19 1981-07-18 Toshiba Corp Turbine blade
US5480284A (en) * 1993-12-20 1996-01-02 General Electric Company Self bleeding rotor blade
EP0726384A1 (fr) * 1995-02-13 1996-08-14 Abb Research Ltd. Aube statorique pour turbines à vapeur
US5803410A (en) * 1995-12-01 1998-09-08 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Skin friction reduction by micro-blowing technique

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 005, no. 162 (M - 092) 17 October 1981 (1981-10-17) *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8336315B2 (en) 2004-02-18 2012-12-25 Siemens Aktiengesellschaft Gas turbine with a compressor housing which is protected against cooling down and method for operating a gas turbine
FR2900692A1 (fr) * 2006-05-05 2007-11-09 Snecma Sa Pale de compresseur comprenant un dispositif d'aspiration

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