EP0556047A1 - Verstärkte Schaufel - Google Patents

Verstärkte Schaufel Download PDF

Info

Publication number
EP0556047A1
EP0556047A1 EP93301003A EP93301003A EP0556047A1 EP 0556047 A1 EP0556047 A1 EP 0556047A1 EP 93301003 A EP93301003 A EP 93301003A EP 93301003 A EP93301003 A EP 93301003A EP 0556047 A1 EP0556047 A1 EP 0556047A1
Authority
EP
European Patent Office
Prior art keywords
vane
trailing edge
wall
aerofoil
convex
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.)
Granted
Application number
EP93301003A
Other languages
English (en)
French (fr)
Other versions
EP0556047B1 (de
Inventor
Ralph Godfrey Jones
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.)
Preci Spark Ltd
Original Assignee
Preci Spark Ltd
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 Preci Spark Ltd filed Critical Preci Spark Ltd
Publication of EP0556047A1 publication Critical patent/EP0556047A1/de
Application granted granted Critical
Publication of EP0556047B1 publication Critical patent/EP0556047B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B3/00—Engines characterised by air compression and subsequent fuel addition
    • F02B3/06—Engines characterised by air compression and subsequent fuel addition with compression ignition

Definitions

  • the present invention relates to a vane for a turbocharger stator as used on large diesel engines, two-stroke and four-stroke.
  • a disadvantage of this cleaning process is that because the exhaust gases are moving at a relatively high speed, the impact of the medium on the vanes can deform the suction surface of the vanes.
  • the present invention seeks to provide an improved vane for a turbine impeller.
  • the present invention provides a vane for a turbocharger stator, the vane being of generally hollow construction with a convex wall and a concave wall meeting at a leading edge and a trailing edge of the vane; and wherein said convex wall is thickened over a portion of its inner surface extending from said trailing edge.
  • a preferred form of vane according to the present invention has internal reinforcements in the form of sheet material pleated in a direction substantially parallel to the trailing and leading edges.
  • a vane according to the present invention enables the use of relatively thin material for the vane walls with localised reinforcement to the area prone to damage by cleaning.
  • this is a cross-section through a vane 10 in the form of an aerofoil for a turbocharger stator for a large diesel engine.
  • the aerofoil has a convex (upper) wall 12 and a concave (lower) wall 14, a leading edge 16 and a trailing edge 18.
  • the aerofoil is manufactured from a thickness of material dictated by the radius of its trailing edge.
  • a typical example of such an aerofoil would have chordal length of 100mm, a thickness of 12mm to 14mm and a trailing edge 18 radius of 0.5mm.
  • a wiggle strip 22 extends the whole length of the aerofoil and is brazed into position to give added strength.
  • the inner surface of the convex wall 12 has a reinforcing plate 20 secured to it, typically by brazing, the reinforcing plate 20 extending from the trailing edge 18 to a point in the region of maximum spacing between the convex and concave walls 12,14.
  • the plate 20 is a shaped reinforcement piece and is designed to give added strength to the area impacted by cleaning medium. It extends into and fills the volume formed by the curvature of the trailing edge 18.
  • the invention therefore, relates to the use of thin material for aerofoils with localised reinforcement to the area prone to damage by cleaning.

Landscapes

  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Rotary Pumps (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Vehicle Body Suspensions (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
EP93301003A 1992-02-13 1993-02-11 Verstärkte Schaufel Expired - Lifetime EP0556047B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB929202982A GB9202982D0 (en) 1992-02-13 1992-02-13 Reinforced vane
GB9202982 1992-02-13

Publications (2)

Publication Number Publication Date
EP0556047A1 true EP0556047A1 (de) 1993-08-18
EP0556047B1 EP0556047B1 (de) 1996-09-04

Family

ID=10710276

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93301003A Expired - Lifetime EP0556047B1 (de) 1992-02-13 1993-02-11 Verstärkte Schaufel

Country Status (5)

Country Link
EP (1) EP0556047B1 (de)
JP (1) JPH05340203A (de)
AT (1) ATE142308T1 (de)
DE (1) DE69304366T2 (de)
GB (2) GB9202982D0 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001038698A1 (de) * 1999-11-24 2001-05-31 Mtu Aero Engines Gmbh Leichtbauteil in verbundbauweise
WO2004055332A1 (en) * 2002-12-18 2004-07-01 Nuovo Pignone Holding S.P.A. Manufacturing method for obtaining high-temperature components for gas turbines and components thus obtained
US8573948B2 (en) 2008-12-17 2013-11-05 Rolls-Royce, Plc Airfoil

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB360230A (en) * 1929-12-04 1931-11-05 Gen Electric Improvements in and relating to methods of preventing the erosion of metallic objects
DE892698C (de) * 1943-05-21 1953-10-08 Messerschmitt Boelkow Blohm Luftgekuehlte Hohlschaufel, insbesondere fuer Gas- und Abgasturbinen
GB716612A (en) * 1951-04-23 1954-10-13 Bristol Aeroplane Co Ltd Improvements in or relating to hollow blades for turbines or compressors
FR2559422A1 (fr) * 1984-02-13 1985-08-16 Gen Electric Element a profil de pale creux composite muni d'une structure support interne ondulee et son procede de fabrication
US4976587A (en) * 1988-07-20 1990-12-11 Dwr Wind Technologies Inc. Composite wind turbine rotor blade and method for making same

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3269700A (en) * 1964-12-07 1966-08-30 United Aircraft Corp Heat shield for turbine strut
DE1601613A1 (de) * 1967-08-03 1970-12-17 Motoren Turbinen Union Turbinenschaufel,insbesondere Turbinenleitschaufel fuer Gasturbinentriebwerke
US3560107A (en) * 1968-09-25 1971-02-02 Gen Motors Corp Cooled airfoil
GB1320539A (en) * 1970-12-10 1973-06-13 Secr Defence Aerofoil-shaped blade for a fluid flow machine
US4815939A (en) * 1986-11-03 1989-03-28 Airfoil Textron Inc. Twisted hollow airfoil with non-twisted internal support ribs
FR2672338B1 (fr) * 1991-02-06 1993-04-16 Snecma Aube de turbine munie d'un systeme de refroidissement.
GB2254892A (en) * 1991-04-16 1992-10-21 Gen Electric Hollow airfoil.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB360230A (en) * 1929-12-04 1931-11-05 Gen Electric Improvements in and relating to methods of preventing the erosion of metallic objects
DE892698C (de) * 1943-05-21 1953-10-08 Messerschmitt Boelkow Blohm Luftgekuehlte Hohlschaufel, insbesondere fuer Gas- und Abgasturbinen
GB716612A (en) * 1951-04-23 1954-10-13 Bristol Aeroplane Co Ltd Improvements in or relating to hollow blades for turbines or compressors
FR2559422A1 (fr) * 1984-02-13 1985-08-16 Gen Electric Element a profil de pale creux composite muni d'une structure support interne ondulee et son procede de fabrication
US4976587A (en) * 1988-07-20 1990-12-11 Dwr Wind Technologies Inc. Composite wind turbine rotor blade and method for making same

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001038698A1 (de) * 1999-11-24 2001-05-31 Mtu Aero Engines Gmbh Leichtbauteil in verbundbauweise
US6893211B1 (en) 1999-11-24 2005-05-17 Miu Aero Engines Gmbh Lightweight structural component having a sandwich structure
WO2004055332A1 (en) * 2002-12-18 2004-07-01 Nuovo Pignone Holding S.P.A. Manufacturing method for obtaining high-temperature components for gas turbines and components thus obtained
CN100390378C (zh) * 2002-12-18 2008-05-28 诺沃·皮戈农控股公司 燃气轮机的高温部件的制造方法以及由此获得的部件
US8573948B2 (en) 2008-12-17 2013-11-05 Rolls-Royce, Plc Airfoil

Also Published As

Publication number Publication date
GB2264149A (en) 1993-08-18
GB9202982D0 (en) 1992-03-25
EP0556047B1 (de) 1996-09-04
GB9302318D0 (en) 1993-03-24
DE69304366D1 (de) 1996-10-10
ATE142308T1 (de) 1996-09-15
DE69304366T2 (de) 1997-06-05
JPH05340203A (ja) 1993-12-21
GB2264149B (en) 1995-07-05

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