US20090238692A1 - Blade of a turbo machine - Google Patents

Blade of a turbo machine Download PDF

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Publication number
US20090238692A1
US20090238692A1 US12/014,268 US1426808A US2009238692A1 US 20090238692 A1 US20090238692 A1 US 20090238692A1 US 1426808 A US1426808 A US 1426808A US 2009238692 A1 US2009238692 A1 US 2009238692A1
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US
United States
Prior art keywords
blade
supporting structure
regard
blade according
optimization
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
US12/014,268
Other languages
English (en)
Inventor
Dirk Buchler
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.)
Voith Turbo Advanced Propeller Technologies GmbH and Co KG
Original Assignee
Air Fertigung Technologie GmbH and Co KG
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 Air Fertigung Technologie GmbH and Co KG filed Critical Air Fertigung Technologie GmbH and Co KG
Assigned to AIR FERTIGUNG-TECHNOLOGIE GMBH & CO. KG reassignment AIR FERTIGUNG-TECHNOLOGIE GMBH & CO. KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BUCHLER, DIRK
Publication of US20090238692A1 publication Critical patent/US20090238692A1/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
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • 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
    • F05D2250/60—Structure; Surface texture
    • 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
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a blade for a turbo machine.
  • turbo machines for example turbines, pumps, drive rotors as components of marine engines.
  • the blades of such machines serve the purpose of torque transmission. Either the forces of a streaming medium act on the blade, as for example in the case of a water turbine, or the blade exerts forces on the flowing medium, as for example in the case of ship propellers.
  • GB 1 345 835 describes a blade for a turbo machine.
  • the blade is build of flexible walls and is inflatable.
  • GB 1 404 665 shows a blade for a gas turbine.
  • the region of the blade that is flowed against is formed of a flexible wall which flows around a hollow space.
  • a pressure medium can be introduced into the hollow space, so that the flexible wall deforms.
  • the shape of a blade is decisive for the efficiency of the torque transfer.
  • the rotor blade is formed in such a way that it exhibits quite specific profile sections adapted to the operating conditions of the turbo machine.
  • the operating conditions change, however, so that the selected profile section forms of the blades only constitute a compromise.
  • the external flow of the individual blades is only optimal in the case of a specified operating state. If the parameters of such an operating state change—throughput, speed of the flowing medium etc.—this has a disadvantageous effect on the efficiency of the turbo machine as well as having a disadvantageous effect on the cavitation tendency.
  • There are ship propellers which are equipped with symmetrically shaped propeller blades. Because of this a compromise for forward and backward motion is aimed at. This compromise is however not optimal, since efficiency losses of up to 25% arise, compared to a propeller whose blades are optimized for a specified direction of thrust.
  • the invention is based on the object of designing a blade of a turbo machine in such a way that it works optimally to a great extent even in the case of different operating conditions.
  • Such blades have the property of automatically adapting the form of the concerned supporting surface of the blade to the respective operating conditions. This relates in particular to the curvature of the supporting surface. With this it is possible to optimize the power conversion increase the efficiency of the turbo machine.
  • the blade in accordance with the invention comprises hence an internal supporting structure and an elastic cover surrounding the supporting structure, said cover being in contact with fluid in the case of operation.
  • the supporting structure exhibits a contour which corresponds to the contour of a conventional blade.
  • the profile of the supporting structure is not necessarily optimized with regard to specified operating conditions.
  • the profile can—with regard to the two lateral faces—be symmetrical and—in a cross-section vertical to the two lateral areas lateral faces—exhibit the shape of a lance point.
  • a flowable inflating medium is placed between the elastic cover and the supporting structure. This can be located on one side or on the other side. Depending on which side it is located on, the part of the elastic cover located there will be inflated and hence more greatly curved than on the other side.
  • Measures can be taken in order to facilitate an overflowing of the inflating medium from the one side of the blade to the other.
  • Perforations in the supporting structure for example come into consideration as such measures.
  • the one or other space can be supplied pressure medium in variable measure; that is, with variable quantity and under variable pressure.
  • the supporting structure does not need to be perforated. Rather it has the function of an inside wall.
  • FIG. 1 shows in schematic representation and in a section the blade of a ship propeller in a first approach flow condition.
  • FIG. 2 shows the subject matter of FIG. 1 in a second approach flow condition.
  • the blade 1 depicted in FIG. 1 comprises a supporting structure 2 .
  • Said structure has the contour of a lance point. It is shaped symmetrically with regard to its longitudinal axis.
  • the two outer surfaces of the supporting structure 2 hence have the same course.
  • the supporting structure 2 is surrounded by an elastic cover 3 .
  • Any type of material comes into consideration, for example rubber or plastic.
  • the elastic cover 3 exhibits a certain oversize compared to the supporting structure 2 , so that a space arises on the one or the other side of the blade 1 .
  • FIGS. 1 and 2 show the inflating medium 4 on different sides of the blade 1 .
  • the inflating medium is on the side of the blade turned away from the approach flow side. Simultaneously one sees that the elastic cover 3 is more greatly bulged on the side where the inflating medium 4 is located.
  • the invention is also applicable in the case of blades shaped otherwise.
  • blades can be used that are not shaped symmetrically, as cited above. It is also possible to use the invention in the case of blades whose form or contour can be changed by other measures.
  • FIG. 1 shows the blades 1 of the rotor of the first of two units. In the present case it is a matter of seven blades. However, there could also be more or fewer. As one sees, the free ends of the blades point to the center of the stream unit, so that a clearance remains between the free ends.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/014,268 2007-01-17 2008-01-15 Blade of a turbo machine Abandoned US20090238692A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007002518A DE102007002518B3 (de) 2007-01-17 2007-01-17 Schaufel einer Strömungsmaschine
DE102007002518.3 2007-01-17

Publications (1)

Publication Number Publication Date
US20090238692A1 true US20090238692A1 (en) 2009-09-24

Family

ID=39564188

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/014,268 Abandoned US20090238692A1 (en) 2007-01-17 2008-01-15 Blade of a turbo machine

Country Status (3)

Country Link
US (1) US20090238692A1 (de)
KR (1) KR20080067986A (de)
DE (1) DE102007002518B3 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100143130A1 (en) * 2009-03-26 2010-06-10 Ronald Ralph Cairo Inflatable wind turbine blade and method for forming said rotor blade
US20160176509A1 (en) * 2014-12-23 2016-06-23 Airbus Operations, S.L. Propeller blade for an aircraft engine
CN109441719A (zh) * 2018-12-21 2019-03-08 沈阳航空航天大学 一种薄膜自激励振动式垂直轴风力机叶片
CN113863991A (zh) * 2021-10-20 2021-12-31 中国航发沈阳黎明航空发动机有限责任公司 一种高气动效率的主动控制柔性表面叶片

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3384183A (en) * 1967-05-08 1968-05-21 Braverman Theodore Stanley Inflatable vane

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2139741B1 (de) * 1971-06-03 1975-01-17 Snecma
IT963220B (it) * 1971-11-01 1974-01-10 Gen Electric Paletta a bordo d entrata smussato per la riduzione del rumore parti colarmente per reattori a turboven tilatore

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3384183A (en) * 1967-05-08 1968-05-21 Braverman Theodore Stanley Inflatable vane

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100143130A1 (en) * 2009-03-26 2010-06-10 Ronald Ralph Cairo Inflatable wind turbine blade and method for forming said rotor blade
US7938623B2 (en) * 2009-03-26 2011-05-10 General Electric Company Inflatable wind turbine blade and method for forming said rotor blade
US20160176509A1 (en) * 2014-12-23 2016-06-23 Airbus Operations, S.L. Propeller blade for an aircraft engine
US10023299B2 (en) * 2014-12-23 2018-07-17 Airbus Operations, S.L. Propeller blade for an aircraft engine
CN109441719A (zh) * 2018-12-21 2019-03-08 沈阳航空航天大学 一种薄膜自激励振动式垂直轴风力机叶片
CN113863991A (zh) * 2021-10-20 2021-12-31 中国航发沈阳黎明航空发动机有限责任公司 一种高气动效率的主动控制柔性表面叶片

Also Published As

Publication number Publication date
DE102007002518B3 (de) 2008-07-31
KR20080067986A (ko) 2008-07-22

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Legal Events

Date Code Title Description
AS Assignment

Owner name: AIR FERTIGUNG-TECHNOLOGIE GMBH & CO. KG, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:BUCHLER, DIRK;REEL/FRAME:020613/0996

Effective date: 20080225

STCB Information on status: application discontinuation

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