JP4216781B2 - ターボジェットエンジンの羽根のサポートのための側方向たわみ型羽根間プラットフォーム - Google Patents
ターボジェットエンジンの羽根のサポートのための側方向たわみ型羽根間プラットフォーム Download PDFInfo
- Publication number
- JP4216781B2 JP4216781B2 JP2004221230A JP2004221230A JP4216781B2 JP 4216781 B2 JP4216781 B2 JP 4216781B2 JP 2004221230 A JP2004221230 A JP 2004221230A JP 2004221230 A JP2004221230 A JP 2004221230A JP 4216781 B2 JP4216781 B2 JP 4216781B2
- Authority
- JP
- Japan
- Prior art keywords
- platform
- blade
- central part
- support disk
- interblade
- 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.)
- Active
Links
- 239000002131 composite material Substances 0.000 claims description 2
- 239000007769 metal material Substances 0.000 claims description 2
- 239000012781 shape memory material Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000000704 physical effect Effects 0.000 description 3
- 238000004026 adhesive bonding Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000013589 supplement Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 241000920340 Pion Species 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- 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
- F05D2300/505—Shape memory behaviour
-
- 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
Description
2 羽根
3 羽根間プラットフォーム
4 固定脚
5 中央部分
6、7 側縁
8、9 側方部分
Claims (6)
- ターボジェットエンジンのファンの羽根(2)のサポートディスク(1)のための羽根間プラットフォーム(3)であって、隣接する2枚の羽根(2)の間で前記サポートディスク(1)に連結することができる中央部分(5)と、前記中央部分(5)の2つの側縁(6、7)を延長し、各々が、羽根(2)の衝撃によってたわむことができる2つの側方部分(8、9)とを有し、
前記側方部分(8、9)が、前記中央部分(5)の側縁(6、7)を薄くすることによって製作され、かつ前記中央部分(5)と単体に製作され、少なくとも前記側方部分(8、9)が、形状記憶材料で製作され、前記側方部分(8、9)が、羽根(2)の衝撃によってたわんだ後、羽根(2)が最初の位置に戻ると最初の形状に戻ることができることを特徴とするプラットフォーム。 - 前記中央部分(5)が第1の厚みを有し、さらに前記側方部分(8、9)が前記第1の厚みより小さい第2の厚みを有することを特徴とする、請求項1に記載のプラットフォーム。
- 前記中央部分(5)が第1の変形抵抗を有し、前記側方部分(8、9)が前記第1の変形抵抗より小さな第2の変形抵抗を有することを特徴とする、請求項1または2に記載のプラットフォーム。
- 金属材料で製作されることを特徴とする、請求項1から3のいずれか一項に記載のプラットフォーム。
- 複合材料で製作されることを特徴とする、請求項1から3のいずれか一項に記載のプラットフォーム。
- それぞれ隣接する羽根(2)対の間に差し挟まれた請求項1から5のいずれか一項に記載の複数の羽根間プラットフォーム(3)を有することを特徴とする、羽根のサポートディスク(1)。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0309451A FR2858351B1 (fr) | 2003-07-31 | 2003-07-31 | Plate-forme inter-aubes a flechissement lateral, pour un support d'aubes de turboreacteur |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005054784A JP2005054784A (ja) | 2005-03-03 |
JP4216781B2 true JP4216781B2 (ja) | 2009-01-28 |
Family
ID=33523036
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004221230A Active JP4216781B2 (ja) | 2003-07-31 | 2004-07-29 | ターボジェットエンジンの羽根のサポートのための側方向たわみ型羽根間プラットフォーム |
Country Status (9)
Country | Link |
---|---|
US (1) | US7153099B2 (ja) |
EP (1) | EP1503044B1 (ja) |
JP (1) | JP4216781B2 (ja) |
CA (1) | CA2475148C (ja) |
DE (1) | DE602004007071T2 (ja) |
ES (1) | ES2287668T3 (ja) |
FR (1) | FR2858351B1 (ja) |
RU (1) | RU2299992C2 (ja) |
UA (1) | UA83623C2 (ja) |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0802834D0 (en) * | 2008-02-18 | 2008-03-26 | Rolls Royce Plc | Annulus filler |
US8616849B2 (en) * | 2009-02-18 | 2013-12-31 | Pratt & Whitney Canada Corp. | Fan blade platform |
US8568102B2 (en) * | 2009-02-18 | 2013-10-29 | Pratt & Whitney Canada Corp. | Fan blade anti-fretting insert |
US9200593B2 (en) * | 2009-08-07 | 2015-12-01 | Hamilton Sundstrand Corporation | Energy absorbing fan blade spacer |
US8066479B2 (en) * | 2010-04-05 | 2011-11-29 | Pratt & Whitney Rocketdyne, Inc. | Non-integral platform and damper for an airfoil |
GB201020857D0 (en) | 2010-12-09 | 2011-01-26 | Rolls Royce Plc | Annulus filler |
US8777576B2 (en) * | 2011-08-22 | 2014-07-15 | General Electric Company | Metallic fan blade platform |
FR2987086B1 (fr) * | 2012-02-22 | 2014-03-21 | Snecma | Joint lineaire de plateforme inter-aubes |
US11035238B2 (en) | 2012-06-19 | 2021-06-15 | Raytheon Technologies Corporation | Airfoil including adhesively bonded shroud |
FR2992676B1 (fr) * | 2012-06-29 | 2014-08-01 | Snecma | Plateforme inter-aubes pour une soufflante, rotor d'une soufflante et procede de fabrication associe |
US10344601B2 (en) | 2012-08-17 | 2019-07-09 | United Technologies Corporation | Contoured flowpath surface |
US11118463B2 (en) * | 2014-04-11 | 2021-09-14 | Raytheon Technologies Corporation | Electrically grounding fan platforms |
US9926798B2 (en) | 2014-08-13 | 2018-03-27 | Rolls-Royce Corporation | Method for manufacturing composite fan annulus filler having nano-coating |
JP6525130B2 (ja) | 2014-10-07 | 2019-06-05 | 株式会社Ihi | 静翼構造及びこれを用いたターボファンエンジン |
US10156151B2 (en) | 2014-10-23 | 2018-12-18 | Rolls-Royce North American Technologies Inc. | Composite annulus filler |
FR3091563B1 (fr) * | 2019-01-04 | 2023-01-20 | Safran Aircraft Engines | Joint d’étanchéité amélioré de plateforme inter-aubes |
FR3097904B1 (fr) * | 2019-06-26 | 2021-06-11 | Safran Aircraft Engines | Plateforme inter-aube avec caisson sacrificiel |
RU2755447C1 (ru) * | 2020-07-23 | 2021-09-16 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Уплотнительный узел турбины газотурбинного двигателя |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2751189A (en) * | 1950-09-08 | 1956-06-19 | United Aircraft Corp | Blade fastening means |
GB811921A (en) * | 1955-03-10 | 1959-04-15 | Rolls Royce | Improvements relating to manufacture of blading for axial-flow fluid machines |
US3294364A (en) * | 1962-01-02 | 1966-12-27 | Gen Electric | Rotor assembly |
GB1232506A (ja) * | 1969-10-28 | 1971-05-19 | ||
GB2171151B (en) * | 1985-02-20 | 1988-05-18 | Rolls Royce | Rotors for gas turbine engines |
US5222865A (en) * | 1991-03-04 | 1993-06-29 | General Electric Company | Platform assembly for attaching rotor blades to a rotor disk |
FR2679296B1 (fr) * | 1991-07-17 | 1993-10-15 | Snecma | Plate-forme separee inter-aube pour disque ailete de rotor de turbomachine. |
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
GB9209895D0 (en) * | 1992-05-07 | 1992-06-24 | Rolls Royce Plc | Rotors for gas turbine engines |
US5443365A (en) * | 1993-12-02 | 1995-08-22 | General Electric Company | Fan blade for blade-out protection |
FR2743845B1 (fr) * | 1996-01-23 | 1998-02-20 | Snecma | Aube mobile de soufflante a profil de securite |
GB9602129D0 (en) * | 1996-02-02 | 1996-04-03 | Rolls Royce Plc | Rotors for gas turbine engines |
GB9828484D0 (en) * | 1998-12-24 | 1999-02-17 | Rolls Royce Plc | Improvements in or relating to bladed structures for fluid flow propulsion engines |
US6217283B1 (en) * | 1999-04-20 | 2001-04-17 | General Electric Company | Composite fan platform |
GB9915637D0 (en) * | 1999-07-06 | 1999-09-01 | Rolls Royce Plc | A rotor seal |
US6416280B1 (en) * | 2000-11-27 | 2002-07-09 | General Electric Company | One piece spinner |
-
2003
- 2003-07-31 FR FR0309451A patent/FR2858351B1/fr not_active Expired - Fee Related
-
2004
- 2004-07-19 US US10/893,270 patent/US7153099B2/en active Active
- 2004-07-23 EP EP04291887A patent/EP1503044B1/fr active Active
- 2004-07-23 CA CA2475148A patent/CA2475148C/fr active Active
- 2004-07-23 ES ES04291887T patent/ES2287668T3/es active Active
- 2004-07-23 DE DE602004007071T patent/DE602004007071T2/de active Active
- 2004-07-29 JP JP2004221230A patent/JP4216781B2/ja active Active
- 2004-07-30 RU RU2004123583/06A patent/RU2299992C2/ru active
- 2004-07-30 UA UA20040706362A patent/UA83623C2/uk unknown
Also Published As
Publication number | Publication date |
---|---|
FR2858351A1 (fr) | 2005-02-04 |
JP2005054784A (ja) | 2005-03-03 |
CA2475148C (fr) | 2011-09-20 |
US20050276691A1 (en) | 2005-12-15 |
RU2004123583A (ru) | 2006-01-27 |
DE602004007071T2 (de) | 2008-02-21 |
CA2475148A1 (fr) | 2005-01-31 |
UA83623C2 (uk) | 2008-08-11 |
EP1503044B1 (fr) | 2007-06-20 |
FR2858351B1 (fr) | 2006-01-13 |
ES2287668T3 (es) | 2007-12-16 |
EP1503044A1 (fr) | 2005-02-02 |
US7153099B2 (en) | 2006-12-26 |
DE602004007071D1 (de) | 2007-08-02 |
RU2299992C2 (ru) | 2007-05-27 |
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