BR112018002793B1 - Pá de rotor de turbomáquina, disco de pá de peça única, rotor, e, turbomáquina - Google Patents

Pá de rotor de turbomáquina, disco de pá de peça única, rotor, e, turbomáquina Download PDF

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Publication number
BR112018002793B1
BR112018002793B1 BR112018002793-6A BR112018002793A BR112018002793B1 BR 112018002793 B1 BR112018002793 B1 BR 112018002793B1 BR 112018002793 A BR112018002793 A BR 112018002793A BR 112018002793 B1 BR112018002793 B1 BR 112018002793B1
Authority
BR
Brazil
Prior art keywords
blade
segment
height
rotor
tangential
Prior art date
Application number
BR112018002793-6A
Other languages
English (en)
Portuguese (pt)
Other versions
BR112018002793A2 (https=
Inventor
Roger Felipe Montes Parra
Prasaad COJANDE
Original Assignee
Safran Aircraft Engines
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 Safran Aircraft Engines filed Critical Safran Aircraft Engines
Publication of BR112018002793A2 publication Critical patent/BR112018002793A2/pt
Publication of BR112018002793B1 publication Critical patent/BR112018002793B1/pt

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Classifications

    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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

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)
BR112018002793-6A 2015-08-11 2016-08-05 Pá de rotor de turbomáquina, disco de pá de peça única, rotor, e, turbomáquina BR112018002793B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1557660A FR3040071B1 (fr) 2015-08-11 2015-08-11 Aube de rotor de turbomachine
FR1557660 2015-08-11
PCT/FR2016/052043 WO2017025684A1 (fr) 2015-08-11 2016-08-05 Aube de rotor de turbomachine

Publications (2)

Publication Number Publication Date
BR112018002793A2 BR112018002793A2 (https=) 2018-10-02
BR112018002793B1 true BR112018002793B1 (pt) 2023-01-17

Family

ID=54937234

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112018002793-6A BR112018002793B1 (pt) 2015-08-11 2016-08-05 Pá de rotor de turbomáquina, disco de pá de peça única, rotor, e, turbomáquina

Country Status (9)

Country Link
US (1) US10801516B2 (https=)
EP (1) EP3334905B1 (https=)
JP (1) JP6921804B2 (https=)
CN (1) CN108138574B (https=)
BR (1) BR112018002793B1 (https=)
CA (1) CA2994912C (https=)
FR (1) FR3040071B1 (https=)
RU (1) RU2727823C2 (https=)
WO (1) WO2017025684A1 (https=)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10947851B2 (en) * 2018-12-19 2021-03-16 Raytheon Technologies Corporation Local pressure side blade tip lean
US11629599B2 (en) * 2019-11-26 2023-04-18 General Electric Company Turbomachine nozzle with an airfoil having a curvilinear trailing edge
CN116292399A (zh) * 2022-12-31 2023-06-23 中国航发沈阳发动机研究所 一种低噪声风扇转子叶片
WO2024157230A1 (en) * 2023-01-27 2024-08-02 Rasheed C Mohammed Blading system for axial compressors with axially opposing base merged double triangular prism device blades
US12241387B1 (en) * 2023-08-24 2025-03-04 Rtx Corporation Tilted CMC vane arc segment

Family Cites Families (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3127093A (en) * 1964-03-31 Ducted sustaining rotor for aircraft
US1829179A (en) * 1929-01-11 1931-10-27 Westinghouse Electric & Mfg Co Method of making turbine blades
US2752258A (en) * 1955-03-02 1956-06-26 Carborundum Co Silicon nitride-bonded silicon carbide refractories
FR2556409B1 (fr) * 1983-12-12 1991-07-12 Gen Electric Aube perfectionnee pour moteur a turbine a gaz et procede de fabrication
US4585395A (en) 1983-12-12 1986-04-29 General Electric Company Gas turbine engine blade
FR2603953B1 (fr) * 1986-09-12 1991-02-22 Peugeot Aciers Et Outillage Pale profilee d'helice et son application aux motoventilateurs
JP2753382B2 (ja) * 1990-09-17 1998-05-20 株式会社日立製作所 軸流タービン静翼装置及び軸流タービン
JP3697296B2 (ja) * 1995-08-25 2005-09-21 株式会社東芝 タービン動翼
US6071077A (en) * 1996-04-09 2000-06-06 Rolls-Royce Plc Swept fan blade
US6305905B1 (en) * 1999-05-05 2001-10-23 United Technologies Corporation Bolted-on propeller blade
US6331100B1 (en) * 1999-12-06 2001-12-18 General Electric Company Doubled bowed compressor airfoil
FR2853022B1 (fr) * 2003-03-27 2006-07-28 Snecma Moteurs Aube de redresseur a double courbure
US7547186B2 (en) * 2004-09-28 2009-06-16 Honeywell International Inc. Nonlinearly stacked low noise turbofan stator
GB0520850D0 (en) * 2005-10-14 2005-11-23 Rolls Royce Plc Fan static structure
US8292574B2 (en) * 2006-11-30 2012-10-23 General Electric Company Advanced booster system
US8087884B2 (en) * 2006-11-30 2012-01-03 General Electric Company Advanced booster stator vane
US8147207B2 (en) * 2008-09-04 2012-04-03 Siemens Energy, Inc. Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion
US8167567B2 (en) * 2008-12-17 2012-05-01 United Technologies Corporation Gas turbine engine airfoil
FR2969230B1 (fr) 2010-12-15 2014-11-21 Snecma Aube de compresseur a loi d'empilage amelioree
US8702398B2 (en) * 2011-03-25 2014-04-22 General Electric Company High camber compressor rotor blade
US8684698B2 (en) * 2011-03-25 2014-04-01 General Electric Company Compressor airfoil with tip dihedral
US9074483B2 (en) * 2011-03-25 2015-07-07 General Electric Company High camber stator vane
FR2989107B1 (fr) * 2012-04-04 2017-03-31 Snecma Aube de rotor de turbomachine
US9506347B2 (en) * 2012-12-19 2016-11-29 Solar Turbines Incorporated Compressor blade for gas turbine engine
US9284843B2 (en) * 2013-03-13 2016-03-15 The Boeing Company Blade safety mechanism for open rotor engine system
GB201702384D0 (en) * 2017-02-14 2017-03-29 Rolls Royce Plc Gas turbine engine fan blade
GB201702382D0 (en) * 2017-02-14 2017-03-29 Rolls Royce Plc Gas turbine engine fan blade

Also Published As

Publication number Publication date
US10801516B2 (en) 2020-10-13
EP3334905B1 (fr) 2019-12-25
RU2018108196A (ru) 2019-09-13
BR112018002793A2 (https=) 2018-10-02
EP3334905A1 (fr) 2018-06-20
CN108138574A (zh) 2018-06-08
FR3040071A1 (fr) 2017-02-17
JP2018527504A (ja) 2018-09-20
RU2727823C2 (ru) 2020-07-24
RU2018108196A3 (https=) 2019-11-25
CN108138574B (zh) 2020-02-07
CA2994912A1 (fr) 2017-02-16
US20180231017A1 (en) 2018-08-16
FR3040071B1 (fr) 2020-03-27
JP6921804B2 (ja) 2021-08-18
WO2017025684A1 (fr) 2017-02-16
CA2994912C (fr) 2023-10-17

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Legal Events

Date Code Title Description
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 05/08/2016, OBSERVADAS AS CONDICOES LEGAIS