DE102004038930A1 - Blade for gas turbine engines of airplanes comprises a surface with dimples distributed over the blade surface - Google Patents

Blade for gas turbine engines of airplanes comprises a surface with dimples distributed over the blade surface Download PDF

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Publication number
DE102004038930A1
DE102004038930A1 DE102004038930A DE102004038930A DE102004038930A1 DE 102004038930 A1 DE102004038930 A1 DE 102004038930A1 DE 102004038930 A DE102004038930 A DE 102004038930A DE 102004038930 A DE102004038930 A DE 102004038930A DE 102004038930 A1 DE102004038930 A1 DE 102004038930A1
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Germany
Prior art keywords
blade
air
gas
depressions
dimples
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DE102004038930A
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German (de)
Inventor
Johann Aumueller
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Individual
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Individual
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Priority to DE102004038930A priority Critical patent/DE102004038930A1/en
Publication of DE102004038930A1 publication Critical patent/DE102004038930A1/en
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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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0025—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply
    • F15D1/003—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions
    • F15D1/005—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions in the form of dimples
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/10—Influencing flow of fluids around bodies of solid material
    • F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The blade comprises a surface with dimples distributed over the blade surface. The dimples produce tiny wind turbulence which reduce friction losses. The dimples are in the form of hollow sites with openings of increasing width and have edges which influence the flow to the blade surface. An independent claim is also included for the method of reducing friction and thereby increasing the efficiency of the engine.

Description

Die Erfindung betrifft eine Vorrichtung nach dem Oberbegriff des Anspruches 1 sowie ein Verfahren nach dem Oberbegriff des Anspruches 5.The The invention relates to a device according to the preamble of the claim 1 and a method according to the preamble of claim 5.

Gasturbinen-Triebwerke sind Wärmekraftmaschinen, die neben mechanischer Wellenleistung vor allem Schubkraft erzeugen. Dies ist jedoch nur dann möglich, wenn die Austrittsgeschwindigkeit des Gases am Triebwerk größer ist als die Geschwindigkeit am Lufteintritt des Triebwerks. Es ist somit notwendig, dem Arbeitsmittel Energie zuzuführen. Im Verdichter geschieht dies in Form von mechanischer Energie zur Druckerhöhung, in der Brennkammer in Form von Wärmeenergie zur Temperaturerhöhung.Gas turbine engines are heat engines, which generate not only mechanical shaft power, but above all thrust. However, this is only possible when the exit velocity of the gas at the engine is greater as the speed at the air intake of the engine. It is thus necessary to supply energy to the work equipment. In the compressor happens this in the form of mechanical energy for pressure increase, in the combustion chamber in the form of heat energy to increase the temperature.

Im Verdichter wird eine bestimmte Menge an Luft pro Zeiteinheit aus der Atmosphäre angesaugt und aufgrund der divergenten Lauf- und Leitlaufschaufelstellung auf einen bestimmten Wert verdichtet und der Brennkammer zugeführt. Im Turbinenabschnitt wird die aus den Brennkammern angelieferte Druckenergie zunächst in den düsenartigen Kanälen der Leitkranzstufen in Geschwindigkeitsenergie umgewandelt. Die Rotorbeschaufelung entzieht dem Gasstrom einen erheblichen Anteil seiner Energie und setzt sie in mechanische Drehbewegung um, wodurch die Turbine in die Lage versetzt wird, den Verdichter und die Anbaugeräte anzutreiben.in the Compressor emits a certain amount of air per unit of time the atmosphere sucked and due to the divergent running and guide vane position compressed to a certain value and fed to the combustion chamber. in the Turbine section becomes the pressure energy delivered from the combustion chambers first in the nozzle-like Channels of Leitzranzstufen converted into speed energy. The rotor blading withdraws the gas stream a significant portion of its energy and converts them into mechanical rotary motion, causing the turbine in being able to drive the compressor and implements.

Aufgabe der Erfindung ist, die Luftreibung in der Turbine zu reduzieren und dadurch eine höhere Leistung bzw. einen geringeren Treibstoffverbrauch zu erreichen.task The invention is to reduce the air friction in the turbine and thereby a higher performance or to achieve a lower fuel consumption.

Gemäß der Erfindung wird dies dadurch erreicht, dass an der Oberfläche von Triebwerksschaufeln Unstetigkeiten, z.B. in Form von kleinen Vertiefungen, sogenannten Dimples, zumindest über einen Teil der Schaufeloberflächen verteilt angeordnet sind, und dass diese Unstetigkeiten an der Oberfläche in der vorbeiströmenden Luft bzw. dem vorbeiströmenden Gas winzige Luftwirbel erzeugen und die strömungsbedingten Reibungsverluste verringern.According to the invention This is achieved by the fact that on the surface of engine blades Discontinuities, e.g. in the form of small depressions, so-called Dimples, at least about a part of the blade surfaces are distributed, and that these discontinuities in the surface in the flowing past Air or passing by Gas tiny air vortex generate and the flow-related friction losses reduce.

Des weiteren wird gemäß der Erfindung vorgeschlagen, dass an den Schaufeloberflächen auf den umströmten Seiten Luftwirbel erzeugt werden, die an den Rändern von Oberflächenunstetigkeiten bzw. -vertiefungen entstehen. Dabei erzeugen die über die Schaufeloberfläche fließenden Gas- bzw. Luftströmungen an den in den Oberflächen ausgebildeten Vertiefungen bzw. Dimples Verwirbelungen, diese Verwirbelungen lösen sich an den Rändern der Vertiefungen ab und die Wirbel, die als Transportmittel für die Gas- bzw. Luftströmung wirken, verringern die Reibung zwischen den Luft- bzw. Gasströmen und der Schaufeloberfläche.Of Another is according to the invention suggested that on the blade surfaces on the sides flow around Air vortex generated at the edges of surface discontinuities or pits emerge. The gas flowing over the blade surface generates or air flows at the in the surfaces formed depressions or Dimples turbulences, these turbulences dissolve on the edges depressions and the vortices, which are used as means of transport for the gas or air flow act, reduce the friction between the air and gas streams and the blade surface.

Die Vertiefungen auf den Schaufeloberflächen sind vorzugsweise in Form von Hohlstellen mit zunehmender Öffnungsweite zur Oberfläche hin ausgebildet. Sie stellen beispielsweise dellenartige Vertiefungen mit einem stetigen und allmählichen Übergang oder einem unstetigen Übergang im Randbereich dar, wobei im Bereich der Vertiefungen der Luftstrom an den Randbereichen Wirbel erzeugt, die ihrerseits Luftpolster bilden, auf denen der Luftstrom mit reduzierter Reibung bewegt wird. Die an den Vertiefungen entstehenden kleinen Luftwirbel wirken dabei nach Art von Kugellagern auf die vorbeiströmende Luft bzw. Gase.The Recesses on the blade surfaces are preferably in shape of voids with increasing opening width to the surface trained. For example, they make dell-like depressions with a steady and gradual transition or a discontinuous transition in the edge region, wherein in the region of the recesses of the air flow generated at the margins vortex, which in turn air cushion form, on which the air flow is moved with reduced friction. The resulting at the wells small air vortex act in the manner of ball bearings on the passing air or gases.

Nachstehend wird die Erfindung in Verbindung mit der Zeichnung anhand eines Ausführungsbeispieles dargestellt.below the invention in conjunction with the drawing with reference to a embodiment shown.

1 zeigt eine schematische Darstellung einer Rotor- oder Stator- Triebswerkschaufel in der erfindungsgemäßen Ausgestaltung, 1 shows a schematic representation of a rotor or stator engine blade in the embodiment according to the invention,

2 die erfindungsgemäße Ausgestaltung in wesentlich vergrößertem Maßstab, und 2 the embodiment of the invention in a much larger scale, and

3 eine abgeänderte Ausführungsform eines erfindungsgemäßen Dimple. 3 a modified embodiment of Dimple invention.

In 1 ist eine mit 1 bezeichnete Rotor- oder Statorschaufel eines Gasturbinen-Triebwerks schematisch angedeutet, das auf der Oberseite 2 und/oder auf der Unterseite 3 kleine Vertiefungen 4 aufweist, die als Dimples bezeichnet werden. In der dargestellten Ausführung nach 1 sind diese Vertiefungen etwa gleichförmig über die gesamte Schaufelunterseite verteilt dargestellt, entsprechend kann die Oberseite 3 ausgebildet sein. Vorzugsweise sind die Vertiefungen 4 insbesondere im Bereich der Vorderkante 5 ausgebildet.In 1 is one with 1 designated rotor or stator blade of a gas turbine engine indicated schematically on the top 2 and / or on the bottom 3 small depressions 4 which are referred to as dimples. In the illustrated embodiment according to 1 These depressions are shown approximately uniformly distributed over the entire blade underside, according to the top 3 be educated. Preferably, the depressions 4 especially in the area of the leading edge 5 educated.

2 zeigt eine vergrößerte Darstellung eines derartigen Dimple. Bei dieser Darstellung ist die Luft- bzw. Gasströmung mit 6 und der an der Unstetigkeitsstelle 7 auftretende bzw. sich lösende Wirbel (sowohl am Zuström- als auch am Abströmende) mit 8 bezeichnet. 2 shows an enlarged view of such Dimple. In this illustration, the air or gas flow with 6 and the one at the discontinuity 7 occurring or dissolving vortex (both at the inflow and the outflow end) with 8th designated.

Claims (6)

Vorrichtung an Schaufeln von Triebwerken, z.B. Gasturbinen-Triebwerken für Flugzeuge, zur Erhöhung der Turbinenleistung, dadurch gekennzeichnet, dass an der Oberfläche von Triebwerksschaufeln Unstetigkeiten z.B. in Form von kleinen Vertiefungen, sogenannten Dimples, zumindest über einen Teil der Schaufeloberflächen verteilt angeordnet sind, und dass diese Unstetigkeiten an den Oberflächen in der vorbeiströmenden Luft bzw. dem vorbeiströmenden Gas winzige Luftwirbel erzeugen, die die strömungsbedingten Reibungsverluste verringern.Device on blades of engines, eg gas turbine engines for aircraft, to increase the turbine power, characterized in that on the surface of engine blades discontinuities, for example in the form of small Wells, so-called dimples, are arranged distributed over at least a part of the blade surfaces, and that these discontinuities on the surfaces in the passing air or the gas flowing past generate tiny air vortex, which reduce the flow-related friction losses. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Vertiefungen in Form von Hohlstellen mit Öffnungen zunehmender Weite zur Oberfläche hin ausgebildet sind.Device according to claim 1, characterized in that that the depressions in the form of voids with openings increasing width to the surface are trained out. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Vertiefungen dellenartige Vertiefungen mit gerundeten Umfangsrändern sind.Device according to claim 1, characterized in that that the depressions are dell-like depressions with rounded peripheral edges. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Vertiefungen im Randbereich zur Schaufeloberfläche die Strömung beeinflussende Kanten aufweisen.Device according to claim 1, characterized in that that the depressions in the edge region to the blade surface the flow have affecting edges. Verfahren zum Verringern der Reibung und damit zur Erhöhung der Leistung bei Triebwerken, deren Schaufeloberflächen von Luft oder Gas umströmt werden, dadurch gekennzeichnet, dass an den umströmten Oberflächen Luftwirbel erzeugt werden, die an den Rändern von Oberflächenunstetigkeiten entstehen.Method for reducing friction and thus for increase the performance of engines whose blade surfaces of Air or gas flows around it, characterized in that air vortexes are generated on the surfaces around which flows the at the edges of surface discontinuities arise. Verfahren nach Anspruch 5, dadurch gekennzeichnet, dass der über die Schaufeloberfläche strömende Gas- bzw. Luftstrom an den in den Oberflächen ausgebildeten Vertiefungen bzw. Dimples Verwirbelungen erzeugt, und dass diese Ver wirbelungen an den Vertiefungen abgelöst werden und als Transportmittel für die Gas- bzw. Luftströmung die Reibung zwischen Luft- bzw. Gasströmen und der Schaufeloberfläche verringern.Method according to claim 5, characterized in that that over the blade surface flowing Gas or air flow at the recesses formed in the surfaces or Dimples turbulence generated, and that these Ver vortexes replaced the wells be and as a means of transport for the gas or air flow reduce the friction between air or gas flows and the blade surface.
DE102004038930A 2004-08-11 2004-08-11 Blade for gas turbine engines of airplanes comprises a surface with dimples distributed over the blade surface Withdrawn DE102004038930A1 (en)

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DE102004038930A DE102004038930A1 (en) 2004-08-11 2004-08-11 Blade for gas turbine engines of airplanes comprises a surface with dimples distributed over the blade surface

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DE102004038930A DE102004038930A1 (en) 2004-08-11 2004-08-11 Blade for gas turbine engines of airplanes comprises a surface with dimples distributed over the blade surface

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008136697A1 (en) * 2007-05-04 2008-11-13 Siemens Aktiengesellschaft Method and apparatus for flow control of a gas
JP2012241732A (en) * 2011-05-16 2012-12-10 Toshiba Corp Airflow control device, and airflow control method
EP3543463A3 (en) * 2018-03-22 2019-10-16 United Technologies Corporation Strut for a gas turbine engine
IT202100000296A1 (en) * 2021-01-08 2022-07-08 Gen Electric TURBINE ENGINE WITH VANE HAVING A SET OF DIMPLES

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008136697A1 (en) * 2007-05-04 2008-11-13 Siemens Aktiengesellschaft Method and apparatus for flow control of a gas
JP2012241732A (en) * 2011-05-16 2012-12-10 Toshiba Corp Airflow control device, and airflow control method
US9297260B2 (en) 2011-05-16 2016-03-29 Kabushiki Kaisha Toshiba Airflow control device and airflow control method
EP3543463A3 (en) * 2018-03-22 2019-10-16 United Technologies Corporation Strut for a gas turbine engine
US10808540B2 (en) 2018-03-22 2020-10-20 Raytheon Technologies Corporation Case for gas turbine engine
IT202100000296A1 (en) * 2021-01-08 2022-07-08 Gen Electric TURBINE ENGINE WITH VANE HAVING A SET OF DIMPLES
CN114753889A (en) * 2021-01-08 2022-07-15 通用电气公司 Turbine engine having an airfoil with a set of dimples
US11933193B2 (en) 2021-01-08 2024-03-19 Ge Avio S.R.L. Turbine engine with an airfoil having a set of dimples

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Effective date: 20110812