EP0556047A1 - Aube renforcée - Google Patents

Aube renforcée 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
German (de)
English (en)
Other versions
EP0556047B1 (fr
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/fr
Application granted granted Critical
Publication of EP0556047B1 publication Critical patent/EP0556047B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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)
  • Vehicle Body Suspensions (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
EP93301003A 1992-02-13 1993-02-11 Aube renforcée Expired - Lifetime EP0556047B1 (fr)

Applications Claiming Priority (2)

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

Publications (2)

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

Family

ID=10710276

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93301003A Expired - Lifetime EP0556047B1 (fr) 1992-02-13 1993-02-11 Aube renforcée

Country Status (5)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001038698A1 (fr) * 1999-11-24 2001-05-31 Mtu Aero Engines Gmbh Composant leger du type composite
WO2004055332A1 (fr) * 2002-12-18 2004-07-01 Nuovo Pignone Holding S.P.A. Procede pour produire des composants haute temperature pour des turbines a gaz et composants ainsi obtenus
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 (fr) * 1999-11-24 2001-05-31 Mtu Aero Engines Gmbh Composant leger du type composite
US6893211B1 (en) 1999-11-24 2005-05-17 Miu Aero Engines Gmbh Lightweight structural component having a sandwich structure
WO2004055332A1 (fr) * 2002-12-18 2004-07-01 Nuovo Pignone Holding S.P.A. Procede pour produire des composants haute temperature pour des turbines a gaz et composants ainsi obtenus
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
GB9202982D0 (en) 1992-03-25
GB2264149B (en) 1995-07-05
GB9302318D0 (en) 1993-03-24
DE69304366T2 (de) 1997-06-05
JPH05340203A (ja) 1993-12-21
GB2264149A (en) 1993-08-18
EP0556047B1 (fr) 1996-09-04
ATE142308T1 (de) 1996-09-15
DE69304366D1 (de) 1996-10-10

Similar Documents

Publication Publication Date Title
US6524074B2 (en) Gas turbine engine blade
US5797725A (en) Gas turbine engine vane and method of manufacture
US8043063B2 (en) Intentionally mistuned integrally bladed rotor
EP0801230B2 (fr) Aube de soufflante recourbée
US5816210A (en) Structure of an exhaust port in an internal combustion engine
EP2154333A2 (fr) Aube refroidie et ensemble de turbine associé
EP1541806B1 (fr) Système d'étanchéité amélioré pour les extrémités d'aubes mobiles de turbomachine
US4512718A (en) Tandem fan stage for gas turbine engines
EP1312755A2 (fr) Profil d'aube pour une deuxième étage de turbine
US20060280614A1 (en) Rotor blade for a wind power station
EP0902165A3 (fr) Aube creuse résistante aux impacts
EP0916811A3 (fr) Extrémité rainurée d'aube de turbine
US5509783A (en) Reinforced vane
EP1065344A3 (fr) Orifices et rainures de refroidissement pour aubes de turbines
EP0924389A3 (fr) Aube de guidage variable pour l'entrée d'une turbine à gaz
CA2569026A1 (fr) Configuration de paroi de machine a flux axial, et turbine a gaz
EP0874132A3 (fr) Joint d'étanchéité pour les interstices entre des aubes de soufflante
EP1321628A3 (fr) Aube de turbine de stateur d'une turbine à gaz et méthode de fabrication
GB2427659A (en) Aerofoil blade and rotor arrangement
EP1217173B2 (fr) Aube de guidage pour turbomachines
JP2003003802A (ja) ターボ機械
EP0556047B1 (fr) Aube renforcée
US6358013B1 (en) Turbine blade and manufacture thereof
JP4531268B2 (ja) ターボ機械翼
CN1734060A (zh) 涡轮叶片的外展支壁

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH DE DK FR GB IT LI NL SE

17P Request for examination filed

Effective date: 19940214

17Q First examination report despatched

Effective date: 19950317

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE CH DE DK FR GB IT LI NL SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 19960904

Ref country code: LI

Effective date: 19960904

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.

Effective date: 19960904

Ref country code: FR

Effective date: 19960904

Ref country code: DK

Effective date: 19960904

Ref country code: CH

Effective date: 19960904

Ref country code: BE

Effective date: 19960904

Ref country code: AT

Effective date: 19960904

REF Corresponds to:

Ref document number: 142308

Country of ref document: AT

Date of ref document: 19960915

Kind code of ref document: T

REF Corresponds to:

Ref document number: 69304366

Country of ref document: DE

Date of ref document: 19961010

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19961204

EN Fr: translation not filed
NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20030212

Year of fee payment: 11

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20030220

Year of fee payment: 11

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040211

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040901

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20040211