EP0291407B1 - Bewegbare Gebläseschaufel mit einer Schneidkante am Ende - Google Patents

Bewegbare Gebläseschaufel mit einer Schneidkante am Ende Download PDF

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Publication number
EP0291407B1
EP0291407B1 EP88401144A EP88401144A EP0291407B1 EP 0291407 B1 EP0291407 B1 EP 0291407B1 EP 88401144 A EP88401144 A EP 88401144A EP 88401144 A EP88401144 A EP 88401144A EP 0291407 B1 EP0291407 B1 EP 0291407B1
Authority
EP
European Patent Office
Prior art keywords
blade
fan
axis
tip
edge
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.)
Expired - Lifetime
Application number
EP88401144A
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English (en)
French (fr)
Other versions
EP0291407A1 (de
Inventor
Patrick Louis Eugène Girault
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0291407A1 publication Critical patent/EP0291407A1/de
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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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator

Definitions

  • the invention relates to a movable blade of a turbojet fan.
  • Modern turbofan engines of the double flow type usually include a compression assembly, commonly designated by the word blower and comprising at least one rotor stage of movable blades at the outlet of which the compressed air is subdivided into two flows: a primary flow which enters the following compression assemblies before passing into a combustion chamber to constitute a hot flow and a secondary flow which enters a so-called secondary annular channel and which in the absence of any heating, in particular in the civil applications of turbojets , constitutes a cold flow, the fan thus used is said to be ducted.
  • the aerodynamic performance of the fan is directly linked to the seal produced between the end of the movable blade and the corresponding internal fixed wall of the fan casing.
  • the internal wall of the casing, opposite the ends of the moving blades usually includes a wear and sealing lining, called abradable.
  • the object of the invention is to improve the results which have been observed during these contacts between the end of the mobile fan blade and the abradable lining of the associated casing.
  • a solution previously implemented in order to ensure the seal between the blade tip and the housing and to try to obtain an acceptable operation during the friction contacts consisted in machining at the end of the blade of the blade a tongue thin over the entire width of the blade of the blade profile, said tongue having to ensure good penetration into the abradable lining.
  • Figures 1a, 1b and 1c of the accompanying drawings show an example of this previous embodiment.
  • the tongue 1 of the blade 2 of a blade 3 is opposite the abradable lining 4 of a casing 5.
  • FR-A-2 459 363 also envisages certain problems encountered during the friction of the blade ends against the wall of the casing and seeks more precisely the axial stabilization of the blades by a preferred orientation of the resulting force developed during contact.
  • a serrated profile associated with a particular geometry is obtained by means of recesses made on the lower surface of the blade.
  • a movable blade of a turbojet fan according to the invention is characterized in that the face of the radially outer end of the blade of the blade is profiled according to a radius centered at a point situated, on the one hand, in front of the radial axis of said blade placed in the mounting position on the fan, that is to say in the offset position on the pressure side of the blade relative to said axis and, on the other hand, beyond the motor axis with respect to said dawn.
  • the edge on the lower side of the radially external end of the blade of the blade forms a cutting edge capable of penetrating into an abradable lining of the internal wall of the fan casing and said end present, as a result of said shelving.
  • a draft angle whose value is between four and five degrees of angle.
  • FIG. 2a similarly to FIG. 1a previously described, 4 designates the abradable lining of the internal wall of a casing 5 of a turbojet fan.
  • a blade of a movable fan blade whose radially outer part is shown in FIG. 2a is designated by 10 and its end by 11; 12 designates the lower edge of the blade and 13 designates the upper edge of the blade.
  • the entire blade 14 is shown in Figure 2b and Figure 2c shows a partial view in the direction of the arrow F of the blade 14 of Figure 2b.
  • the end 11 of the blade 10 of the blade 14 forms with the lower surface edge 12 an edge 15.
  • the end line 11 of the blade 14 forms with a line oriented parallel to the wall of the casing, at the edge 15, an angle whose value is four to five degrees of angle.
  • This draft angle is obtained by the shelving of the end 11 of the blade 14, centered at a point R of which an example of determination is given in FIG. 3. If we consider the axis of rotation of the motor shown in M'M and the radial axis of the blade 14 in the mounting position on the fan in X ' X, said point R is located in front of the X'X axis, that is, in the offset position on the side of the lower surface edge 12 of the blade 14 and both beyond the motor axis M'M relative to the 'dawn 14 considered.
  • the end profile 11 of the blade 14 is radiated with the point as its center. R thus defined, distinct from point C.
  • the end 11 of the blade 14 therefore presents itself, as visible in FIG. 2a, relative to the abradable lining 4 of the casing 5, like the end of a tool for section having an edge located at 15 on the side of the lower surface edge 12 of the blade and a clearance angle a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

1. Bewegliche Schaufel für den Verdichter eines Luftstrahltriebwerks, dadurch gekennzeichnet, daß das Profil der Seite des radial äußeren Endbereichs (11) des Blatts (10) der Schaufel (14) entsprechend einem Radius gestaltet ist, der in einem Punkt R zentriert ist, der einerseits vor der radialen Achse X'X der in Montageposition an dem Verdichter plazierten Schaufel (14), d.h. in einer gegenüber der genannten Achse X'X zur Hohlseite (12) der Schaufel versetzten Position, und andererseits bezogen auf die Schaufel (14), jenseits der Antriebsachse M'M liegt.
2. Bewegliche Schaufel für den Verdichter eines Luftstrahltriebwerks nach Anspruch 1, bei der die auf der Hohlseite liegende Kante (15) des radial außen liegenden Endbereichs (11) des Blatts (10) der Schaufel (14) eine Schneidkante (15) bildet, die in einen abtragbaren Belag (4) auf der Innenwandung des Verdichtergehäuses eindringen kann, und bei der der dieser Endbereich (11) infolge der genannten Radiusgestaltung seines Profils einen Freiwinkel a hat, dessen Wert zwischen 4° und 5° liegt.
EP88401144A 1987-05-13 1988-05-11 Bewegbare Gebläseschaufel mit einer Schneidkante am Ende Expired - Lifetime EP0291407B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8706671A FR2615254A1 (fr) 1987-05-13 1987-05-13 Aube mobile de soufflante comportant une depouille en extremite
FR8706671 1987-05-13

Publications (2)

Publication Number Publication Date
EP0291407A1 EP0291407A1 (de) 1988-11-17
EP0291407B1 true EP0291407B1 (de) 1990-10-24

Family

ID=9351022

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88401144A Expired - Lifetime EP0291407B1 (de) 1987-05-13 1988-05-11 Bewegbare Gebläseschaufel mit einer Schneidkante am Ende

Country Status (4)

Country Link
US (1) US4957411A (de)
EP (1) EP0291407B1 (de)
DE (1) DE3860869D1 (de)
FR (1) FR2615254A1 (de)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5476363A (en) * 1993-10-15 1995-12-19 Charles E. Sohl Method and apparatus for reducing stress on the tips of turbine or compressor blades
US6217277B1 (en) 1999-10-05 2001-04-17 Pratt & Whitney Canada Corp. Turbofan engine including improved fan blade lining
DE10047307A1 (de) * 2000-09-25 2002-08-01 Alstom Switzerland Ltd Dichtungsanordnung
FR2825411B1 (fr) * 2001-05-31 2003-09-19 Snecma Moteurs Aube de turbine avec lechette d'etancheite
US7001144B2 (en) * 2003-02-27 2006-02-21 General Electric Company Gas turbine and method for reducing bucket tip shroud creep rate
FR2891594A1 (fr) * 2005-09-30 2007-04-06 Snecma Sa Aube de compresseur a sommet chanfreine
JP4830812B2 (ja) 2006-11-24 2011-12-07 株式会社Ｉｈｉ 圧縮機動翼
US8172518B2 (en) * 2006-12-29 2012-05-08 General Electric Company Methods and apparatus for fabricating a rotor assembly
EP1953344B1 (de) * 2007-02-05 2012-04-11 Siemens Aktiengesellschaft Turbinenschaufel
US8092178B2 (en) * 2008-11-28 2012-01-10 Pratt & Whitney Canada Corp. Turbine blade for a gas turbine engine
US8657570B2 (en) 2009-06-30 2014-02-25 General Electric Company Rotor blade with reduced rub loading
US8662834B2 (en) 2009-06-30 2014-03-04 General Electric Company Method for reducing tip rub loading
WO2011002570A1 (en) * 2009-06-30 2011-01-06 General Electric Company Rotor blade and method for reducing tip rub loading
EP2309097A1 (de) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil und zugehörige Leitschaufel, Laufschaufel, Gasturbine und Strömungsmaschine
FR2962762B1 (fr) * 2010-07-19 2014-04-11 Snecma Aube de compresseur dans une turbomachine
GB2483059A (en) * 2010-08-23 2012-02-29 Rolls Royce Plc An aerofoil blade with a set-back portion
GB201017797D0 (en) * 2010-10-21 2010-12-01 Rolls Royce Plc An aerofoil structure
CN102116316A (zh) * 2010-12-24 2011-07-06 苏州雅典娜科技有限公司 一种轴流泵
US20130149163A1 (en) * 2011-12-13 2013-06-13 United Technologies Corporation Method for Reducing Stress on Blade Tips
GB201222973D0 (en) * 2012-12-19 2013-01-30 Composite Technology & Applic Ltd An aerofoil structure
US9932839B2 (en) 2014-06-04 2018-04-03 United Technologies Corporation Cutting blade tips
US11066937B2 (en) * 2014-06-04 2021-07-20 Raytheon Technologies Corporation Cutting blade tips
GB201410264D0 (en) * 2014-06-10 2014-07-23 Rolls Royce Plc An assembly
CN105422510A (zh) * 2014-08-25 2016-03-23 中国航空工业集团公司沈阳发动机设计研究所 一种带支板的机匣结构设计方法
JP6462332B2 (ja) * 2014-11-20 2019-01-30 三菱重工業株式会社 タービン動翼及びガスタービン

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE560589C (de) * 1932-10-04 Franz Burghauser Dipl Ing Einrichtung zur Verminderung des Schaufelspaltverlustes von Dampf- und Gasturbinen
FR349641A (fr) * 1904-05-24 1905-06-07 Dampf Turbinen System Brown Bo Dispositif d'aubes pour turbines à vapeur à réaction
US2459850A (en) * 1945-12-10 1949-01-25 Westinghouse Electric Corp Turbine apparatus
US3053694A (en) * 1961-02-20 1962-09-11 Gen Electric Abradable material
GB1419381A (en) * 1972-03-09 1975-12-31 Rolls Royce Fan for gas turbine engines
JPS5566602A (en) * 1978-11-10 1980-05-20 Kobe Steel Ltd Impeller of turbo machine
US4274806A (en) * 1979-06-18 1981-06-23 General Electric Company Staircase blade tip
US4621979A (en) * 1979-11-30 1986-11-11 United Technologies Corporation Fan rotor blades of turbofan engines
US4566700A (en) * 1982-08-09 1986-01-28 United Technologies Corporation Abrasive/abradable gas path seal system
US4478552A (en) * 1982-11-08 1984-10-23 Thompson Stanley E Method and apparatus for fan blade tip clearance

Also Published As

Publication number Publication date
EP0291407A1 (de) 1988-11-17
FR2615254A1 (fr) 1988-11-18
DE3860869D1 (de) 1990-11-29
US4957411A (en) 1990-09-18

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