JP2008163949A - ロータアセンブリを製造するための装置 - Google Patents
ロータアセンブリを製造するための装置 Download PDFInfo
- Publication number
- JP2008163949A JP2008163949A JP2007338450A JP2007338450A JP2008163949A JP 2008163949 A JP2008163949 A JP 2008163949A JP 2007338450 A JP2007338450 A JP 2007338450A JP 2007338450 A JP2007338450 A JP 2007338450A JP 2008163949 A JP2008163949 A JP 2008163949A
- Authority
- JP
- Japan
- Prior art keywords
- airfoil
- side wall
- blade
- rotor
- rotor assembly
- 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
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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
-
- 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
- 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
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49318—Repairing or disassembling
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49325—Shaping integrally bladed rotor
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】当該エアフォイル42は、第1側壁44と、前縁48および後縁50において第1側壁に結合する第2側壁46と、根元部分54と、端部摩擦の間にエアフォイルに対して生じる半径方向負荷の削減を容易にする角度をなして第1および第2の側壁の間において斜めに延在する端部60を包含する。
【選択図】図3
Description
12 長手方向軸
13 ファンアセンブリ
14 ブースタコンプレッサ
16 コアガスタービンエンジン
18 高圧タービン
20 ロータディスク
22 高圧コンプレッサ
24 燃焼室
26 低圧タービン
28 吸気側
29 第2ドライブシャフト
30 排気側
31 第1ドライブシャフト
32 摩耗性材料
33 隙間
34 内側境界
35 流路
36 外側境界
38 第1撓曲応力個所
40 ロータブレード
42 エアフォイル部分
43 ダブテール
44 第1輪郭側壁
46 第2輪郭側壁
48 前縁
50 後縁
52 翼幅
54 根元部分
55 プラットフォーム
60 端部
62 端部表面
64 凹状エッジ
66 凸状エッジ
80 スタッキング軸
82 平面
140 ブースタコンプレッサブレード
160 ブレード端部
162 端部表面
164 凹状エッジ
166 凸状エッジ
Claims (10)
- ロータアセンブリにおいて使用されるエアフォイル(42)であって:
第1側壁(44)と;
前縁(48)および後縁(50)において前記第1側壁に結合する第2側壁(46)と;
根元部分(54)と;
端部摩擦の間に前記エアフォイルに対して生じる半径方向負荷の削減を容易にする角度をなして前記第1および第2の側壁の間において斜めに延在する端部(60)とを含む、
前記ロータアセンブリにおいて使用されるエアフォイル(42)。 - 前記第1側壁(44)が凹状側壁を包含し、前記第2側壁(46)が凸状側壁を包含する、
請求項1記載のエアフォイル(42)。 - スタッキング軸(80)と前記スタッキング軸に対して実質的に垂直な角度をなす平面とを更に包含し、前記端部の角度が前記平面(82)に対して5°から15°である、
請求項1記載のエアフォイル(42)。 - 内側流路および外側流路を更に包含する、
請求項1記載のエアフォイル。 - 前記内側流路が外側流路に対して平行ではない、
請求項4記載のエアフォイル(42)。 - ケーシングと前記第1側壁(44)の間において測定される間隔が、ケーシングと前記第2側壁(46)の間において測定される間隔より小さい、
請求項1記載のエアフォイル(42)。 - 前記端部の角度がレーキング処理により形成される、
請求項1記載のエアフォイル(42)。 - 摩耗性ケーシングがロータアセンブリの回りにおいて周方向に延在し、前記端部の角度により、前記第1側壁(44)が摩耗性ケーシングと接触することを容易にしつつ、前記第2側壁(46)が端部摩擦の間に摩耗性ケーシングに接触することを回避する、
請求項1記載のエアフォイル(42)。 - ガスタービンエンジン(10)において使用するロータアセンブリであって:
ロータシャフトと複数のロータブレード(40)を含み、
前記複数のロータブレード(40)が前記ロータシャフトに結合し、各々の前記ロータブレードが、第1側壁(44)と、前縁(48)および後縁(50)において前記第1側壁に結合する第2側壁(46)と、根元部分(54)と、端部摩擦の間に前記エアフォイルに対して生じる半径方向負荷の削減を容易にする角度をなして前記第1および第2の側壁の間において斜めに延在する端部(60)とを包含するエアフォイル部分(42)を包含する、
ロータアセンブリ。 - 前記第1側壁(44)が凹状側壁を有し、前記第2側壁(46)が凸状側壁を包含する、
請求項9記載のロータアセンブリ。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/617,911 US8172518B2 (en) | 2006-12-29 | 2006-12-29 | Methods and apparatus for fabricating a rotor assembly |
US11/617,911 | 2006-12-29 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008163949A true JP2008163949A (ja) | 2008-07-17 |
JP5579965B2 JP5579965B2 (ja) | 2014-08-27 |
Family
ID=39247640
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007338450A Expired - Fee Related JP5579965B2 (ja) | 2006-12-29 | 2007-12-28 | ロータアセンブリを製造するための装置 |
Country Status (4)
Country | Link |
---|---|
US (1) | US8172518B2 (ja) |
EP (1) | EP1942252B1 (ja) |
JP (1) | JP5579965B2 (ja) |
CA (1) | CA2615625C (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2012532268A (ja) * | 2009-06-30 | 2012-12-13 | ゼネラル・エレクトリック・カンパニイ | 先端摩擦荷重を低減するためのロータブレード及び方法 |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2924958B1 (fr) * | 2007-12-14 | 2012-08-24 | Snecma | Aube de turbomachine realisee de fonderie avec un engraissement local de la section de la pale |
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 |
CN101956722B (zh) * | 2010-06-03 | 2016-05-04 | 深圳市超频三科技股份有限公司 | 一种风扇 |
US20130052021A1 (en) * | 2011-08-23 | 2013-02-28 | United Technologies Corporation | Rotor asymmetry |
US9566669B2 (en) | 2012-06-13 | 2017-02-14 | United Technologies Corporation | Tip fabrication for rotor blade or stator vane airfoil |
GB2543327A (en) * | 2015-10-15 | 2017-04-19 | Rolls Royce Plc | Aerofoil tip profiles |
US10385865B2 (en) | 2016-03-07 | 2019-08-20 | General Electric Company | Airfoil tip geometry to reduce blade wear in gas turbine engines |
US10633983B2 (en) | 2016-03-07 | 2020-04-28 | General Electric Company | Airfoil tip geometry to reduce blade wear in gas turbine engines |
US11078588B2 (en) | 2017-01-09 | 2021-08-03 | Raytheon Technologies Corporation | Pulse plated abrasive grit |
GB201900961D0 (en) | 2019-01-24 | 2019-03-13 | Rolls Royce Plc | Fan blade |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS562402A (en) * | 1979-06-18 | 1981-01-12 | Gen Electric | Vane tip for turbo machine |
JPS60192899A (ja) * | 1984-02-06 | 1985-10-01 | ゼネラル・エレクトリツク・カンパニイ | 凹所を設けた圧縮機ケ−シング |
JP2001182694A (ja) * | 1999-11-15 | 2001-07-06 | General Electric Co <Ge> | 耐摩擦性圧縮機段 |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4390320A (en) * | 1980-05-01 | 1983-06-28 | General Electric Company | Tip cap for a rotor blade and method of replacement |
FR2615254A1 (fr) * | 1987-05-13 | 1988-11-18 | Snecma | Aube mobile de soufflante comportant une depouille en extremite |
US4874290A (en) * | 1988-08-26 | 1989-10-17 | Solar Turbines Incorporated | Turbine blade top clearance control system |
DE4122008A1 (de) * | 1991-07-03 | 1993-01-14 | Mtu Muenchen Gmbh | Propfantriebwerk mit gegenlaeufigem niederdruckverdichter (booster) |
US5603603A (en) * | 1993-12-08 | 1997-02-18 | United Technologies Corporation | Abrasive blade tip |
US6095755A (en) * | 1996-11-26 | 2000-08-01 | United Technologies Corporation | Gas turbine engine airfoils having increased fatigue strength |
US6568909B2 (en) * | 2001-09-26 | 2003-05-27 | General Electric Company | Methods and apparatus for improving engine operation |
DE10202810B4 (de) * | 2002-01-25 | 2004-05-06 | Mtu Aero Engines Gmbh | Turbinenlaufschaufel für den Läufer eines Gasturbinentriebwerks |
US6652235B1 (en) * | 2002-05-31 | 2003-11-25 | General Electric Company | Method and apparatus for reducing turbine blade tip region temperatures |
US6652222B1 (en) * | 2002-09-03 | 2003-11-25 | Pratt & Whitney Canada Corp. | Fan case design with metal foam between Kevlar |
US6877956B2 (en) * | 2002-12-23 | 2005-04-12 | General Electric Company | Methods and apparatus for integral radial leakage seal |
US6851926B2 (en) * | 2003-03-07 | 2005-02-08 | General Electric Company | Variable thickness turbine bucket cover and related method |
US7144221B2 (en) * | 2004-07-30 | 2006-12-05 | General Electric Company | Method and apparatus for assembling gas turbine engines |
US7472478B2 (en) * | 2004-10-29 | 2009-01-06 | Honeywell International Inc. | Adaptive machining and weld repair process |
-
2006
- 2006-12-29 US US11/617,911 patent/US8172518B2/en active Active
-
2007
- 2007-12-14 EP EP07123246.6A patent/EP1942252B1/en not_active Not-in-force
- 2007-12-20 CA CA2615625A patent/CA2615625C/en not_active Expired - Fee Related
- 2007-12-28 JP JP2007338450A patent/JP5579965B2/ja not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS562402A (en) * | 1979-06-18 | 1981-01-12 | Gen Electric | Vane tip for turbo machine |
JPS60192899A (ja) * | 1984-02-06 | 1985-10-01 | ゼネラル・エレクトリツク・カンパニイ | 凹所を設けた圧縮機ケ−シング |
JP2001182694A (ja) * | 1999-11-15 | 2001-07-06 | General Electric Co <Ge> | 耐摩擦性圧縮機段 |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2012532268A (ja) * | 2009-06-30 | 2012-12-13 | ゼネラル・エレクトリック・カンパニイ | 先端摩擦荷重を低減するためのロータブレード及び方法 |
Also Published As
Publication number | Publication date |
---|---|
US8172518B2 (en) | 2012-05-08 |
EP1942252A3 (en) | 2010-11-03 |
CA2615625A1 (en) | 2008-06-29 |
EP1942252A2 (en) | 2008-07-09 |
EP1942252B1 (en) | 2014-04-02 |
JP5579965B2 (ja) | 2014-08-27 |
CA2615625C (en) | 2015-12-01 |
US20080159869A1 (en) | 2008-07-03 |
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