US20110189014A1 - Gas turbine and method for varying the aerodynamic shape of a gas turbine blade - Google Patents

Gas turbine and method for varying the aerodynamic shape of a gas turbine blade Download PDF

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Publication number
US20110189014A1
US20110189014A1 US13/003,854 US200913003854A US2011189014A1 US 20110189014 A1 US20110189014 A1 US 20110189014A1 US 200913003854 A US200913003854 A US 200913003854A US 2011189014 A1 US2011189014 A1 US 2011189014A1
Authority
US
United States
Prior art keywords
blade
gas turbine
hot air
shape
turbine according
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.)
Abandoned
Application number
US13/003,854
Other languages
English (en)
Inventor
Sven-J. Hiller
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HILLER, SVEN-J.
Publication of US20110189014A1 publication Critical patent/US20110189014A1/en
Abandoned 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/505—Shape memory behaviour
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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

Definitions

  • the invention relates to a gas turbine having guide blades and rotor blades in the compressor section and turbine section.
  • Gas turbines are used as aircraft propulsion devices in particular and have at least one rotor and at least one stator, and namely both in the compressor region as well as in the turbine region.
  • the rotor blades assigned to the rotor rotate vis-à-vis the stationary housing and the likewise stationary guide blades.
  • Gas turbines are subject to different ambient conditions and flow conditions, which they undergo during operation. Because of these different conditions, it is desirable to temporarily vary the geometric shape of the blades.
  • Various forms of so-called adaptive blades have already been envisaged.
  • One of these options consists of wires made of shape-memory alloys being used on or in a blade to change the shape of the profile. These wires are heated electrically until the abrupt phase change specific to shape-memory alloys occurs. Because of the resulting changing shape of the wires (expansion or contraction), the blade shape is modified.
  • the object of the invention is making a gas turbine available in which the aerodynamic shape change of the blades may take place in a simplified manner.
  • the gas turbine according to the invention has guide blades and rotor blades in the compressor section and turbine section. At least some of the blades have a coating of a shape-memory alloy. At least one channel that optionally directs hot air ends in such a way at one or more coated blades that the hot air causes a phase change of the alloy such that the blade varies its aerodynamic shape.
  • the shape-memory material is applied to a blade by alloying in such a way that a simple and optimal connection is produced between the blade and its coating.
  • Activation of the shape-memory material is not brought about electrically, but via the customary hot air that is available anyway in the case of gas turbines, which is transported to the shape-memory material via at least one hot air channel.
  • the amount of energy transported by the hot air must be sufficient to cause the phase change.
  • a specific quantity of hot air could be directed continuously to the coated blade and then an additional amount of hot air energy could be transported there just for the phase change.
  • hot air is directed to the coated blade or coated blades only when the phase change is supposed to be brought about.
  • a further advantage of the invention is that blowing in air, particularly in the case of a compressor, makes it possible to prevent so-called pumping, which may occur preferably in the partial load range (off-design state). Feeding the hot air also thereby optionally fulfills a dual function, namely improved compressor stabilization along with the blade shape change. In addition, because no electrical energy is required for the phase change, the coated blades may be made of metal.
  • the blades are preferably coated on the outer side with the shape-memory alloy.
  • the blade could also be coated on the inside, namely in that they are designed to be hollow on the inside.
  • the coated blades are compressor blades, with which naturally the temperature is not as high as in the turbine region, whereby great temperature differences may be generated between the hot air feed and the hot air interrupt.
  • the channel or channels start in particular from a downstream compressor stage and direct hot air upstream from this compressor stage.
  • the channel or the channels may end at the housing and from there guide the hot air in the direction of the blades and/or discharge into the interior of the coated blade and blow hot air into the blade.
  • This hot air can then be directed for example via openings to the outer side of the blade, where the coating of the shape-memory alloy is heated abruptly.
  • the coated blades are guide blades and/or rotor blades.
  • the blade which is coated with the shape-memory alloy, is made of metal.
  • hot compressor air is used as the hot air.
  • FIG. 1 is a longitudinal section through a gas turbine according to the invention.
  • FIG. 2 is a schematic longitudinal section through the compressor region of the gas turbine according to FIG. 1 .
  • FIG. 1 depicts a gas turbine having an inlet diffuser 10 , a compressor 12 , a combustion chamber 14 , a turbine 16 and a thrust nozzle 18 , all of which are situated in a housing 20 . Only by way of example, several of the numerous rotor blades 22 are depicted as part of the rotor and guide blades 24 are depicted as part of the stator in the compressor section or turbine section.
  • FIG. 2 shows that the depicted compressor 12 is multi-stage and has an axial design. It is easy to see that the guide blades 24 are connected to the housing 20 and the rotor blades 22 are connected to the rotor 26 .
  • the housing 20 Directly upstream from the so-called blade tip 28 of a rotor blade ring, the housing 20 has several uniformly distributed blow-in openings 30 for hot gas on the circumference.
  • the blow-in openings 30 are the end of one or more channels 32 , which direct hot air upstream from a downstream compressor stage via one or more outlet openings 34 .
  • Arrow 36 symbolizes the hot gases.
  • the channels 32 may also discharge into hollow blades 22 or 24 .
  • Corresponding cavities in the interior of a guide blade 24 are identified by the reference number 38 and are depicted by broken lines.
  • shut-off devices 40 may also be arranged in the channels 36 , which release or interrupt the hot gas flow.
  • the location of these shut-off devices 40 is not restricted to the position indicated in FIG. 2 .
  • Some or all of the guide blades and rotor blades 22 , 24 of one or more stages are provided at least in sections with a coating 42 on the outer side.
  • This coating 42 is provided preferably in the region of the side of the corresponding blades 22 , 24 that faces upstream.
  • the shape-memory alloys are designated as memory-alloy components or memory-alloy materials. These types of material change their structural phases when exceeding or falling short of characteristic temperature values.
  • Possible materials are nickel-titanium alloys, copper-zinc-aluminum alloys or copper-aluminum-nickel alloys for example. Naturally, this enumeration is not conclusive.
  • the coating 42 is applied during the manufacture of the blades 22 , 24 in such a way that no prefabricated part made of a shape-memory alloy must be attached separately.
  • the material of which the blades 22 , 24 are made is preferably a metal alloy.
  • the depicted gas turbine does not have a variable guide baffle, a fact that simplifies the gas turbine in terms of its structure and manufacture.
  • the outer-side coating 42 of a shape-memory alloy may optionally undergo a phase change when the gas turbine is in operation, which is achieved by targeted heating by means of the hot air 36 .
  • hot air is conveyed from downstream compressor stages via the channel or channels 32 to upstream compressor stages, either via the housing 20 and corresponding inlet openings 30 , or via the hollow interior of blades 22 , 24 , whose cavities 38 preferably end on the outer side (particularly on the upstream outer side) of the corresponding blade 22 , 24 .
  • the hot air encountering the coating 42 produces a phase change so that the thin alloy layer contracts or expands. Because the layer is applied to the entire surface of the blade 22 , 24 , the blade 22 , 24 is bent in the desired direction or, more generally, the blade 22 , 24 is deformed elastically, which is naturally reversible.
  • the gas turbine compressor flow is also stabilized, which is especially important for the partial load range. Due to the air blown in, the pumping limit is shifted as far as possible to low throughputs.

Landscapes

  • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/003,854 2008-07-18 2009-07-17 Gas turbine and method for varying the aerodynamic shape of a gas turbine blade Abandoned US20110189014A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102008033783A DE102008033783A1 (de) 2008-07-18 2008-07-18 Gasturbine und Verfahren zum Ändern der aerodynamischen Gestalt einer Gasturbinenschaufel
DE102008033783.8 2008-07-18
PCT/DE2009/000997 WO2010006591A2 (de) 2008-07-18 2009-07-17 Gasturbine und verfahren zum ändern der aerodynamischen gestalt einer gasturbinenschaufel

Publications (1)

Publication Number Publication Date
US20110189014A1 true US20110189014A1 (en) 2011-08-04

Family

ID=41427253

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/003,854 Abandoned US20110189014A1 (en) 2008-07-18 2009-07-17 Gas turbine and method for varying the aerodynamic shape of a gas turbine blade

Country Status (5)

Country Link
US (1) US20110189014A1 (de)
EP (1) EP2304184A2 (de)
CA (1) CA2730892A1 (de)
DE (1) DE102008033783A1 (de)
WO (1) WO2010006591A2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102400718A (zh) * 2011-11-23 2012-04-04 哈尔滨工业大学 可变形的涡扇发动机NiTi形状记忆合金叶片
US20130167552A1 (en) * 2012-01-04 2013-07-04 General Electric Company Exhaust strut and turbomachine incorprating same
CN113186530A (zh) * 2020-01-10 2021-07-30 通用电气公司 用于制造叶片结构的方法
US11441545B2 (en) 2020-02-25 2022-09-13 General Electric Company Tungsten-based erosion-resistant leading edge protection cap for rotor blades

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6015263A (en) * 1998-03-31 2000-01-18 Motorola, Inc. Fluid moving device and associated method
US20060018761A1 (en) * 2004-07-02 2006-01-26 Webster John R Adaptable fluid flow device
US8011882B2 (en) * 2005-09-24 2011-09-06 Rolls-Royce Plc Vane assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19909899A1 (de) * 1999-03-06 2000-09-07 Abb Research Ltd Schaufeln mit veränderbarer Profilgeometrie
US7367776B2 (en) * 2005-01-26 2008-05-06 General Electric Company Turbine engine stator including shape memory alloy and clearance control method
DE102005052466A1 (de) * 2005-11-03 2007-05-10 Mtu Aero Engines Gmbh Mehrstufiger Verdichter für eine Gasturbine mit Abblasöffnungen und Einblasöffnungen zum Stabilisieren der Verdichterströmung
EP1820940A1 (de) * 2006-02-16 2007-08-22 Siemens Aktiengesellschaft Strömungsmaschine mit einer Beschichtung von Laufschaufeln mit einer Formgedächtnislegierung und Verwendung einer Formgedächtnislegierung für eine solche Strömungsmaschine.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6015263A (en) * 1998-03-31 2000-01-18 Motorola, Inc. Fluid moving device and associated method
US20060018761A1 (en) * 2004-07-02 2006-01-26 Webster John R Adaptable fluid flow device
US8011882B2 (en) * 2005-09-24 2011-09-06 Rolls-Royce Plc Vane assembly

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102400718A (zh) * 2011-11-23 2012-04-04 哈尔滨工业大学 可变形的涡扇发动机NiTi形状记忆合金叶片
US20130167552A1 (en) * 2012-01-04 2013-07-04 General Electric Company Exhaust strut and turbomachine incorprating same
CN113186530A (zh) * 2020-01-10 2021-07-30 通用电气公司 用于制造叶片结构的方法
US11486349B2 (en) 2020-01-10 2022-11-01 General Electric Company Methods for manufacturing blade structures
US11441545B2 (en) 2020-02-25 2022-09-13 General Electric Company Tungsten-based erosion-resistant leading edge protection cap for rotor blades

Also Published As

Publication number Publication date
WO2010006591A3 (de) 2010-11-18
DE102008033783A1 (de) 2010-01-21
WO2010006591A2 (de) 2010-01-21
EP2304184A2 (de) 2011-04-06
CA2730892A1 (en) 2010-01-21

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Legal Events

Date Code Title Description
AS Assignment

Owner name: MTU AERO ENGINES GMBH, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:HILLER, SVEN-J.;REEL/FRAME:026126/0176

Effective date: 20110121

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION