JP5579965B2 - 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
- JP5579965B2 JP5579965B2 JP2007338450A JP2007338450A JP5579965B2 JP 5579965 B2 JP5579965 B2 JP 5579965B2 JP 2007338450 A JP2007338450 A JP 2007338450A JP 2007338450 A JP2007338450 A JP 2007338450A JP 5579965 B2 JP5579965 B2 JP 5579965B2
- Authority
- JP
- Japan
- Prior art keywords
- side wall
- airfoil
- plane
- angle
- casing
- 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.)
- Expired - Fee Related
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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)
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:
凹状の第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、凸状の第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ように、前記第1の側壁に対して鋭角を形成し且つ前記第2の側壁に対して鈍角を形成するよう方向づけられた端部表面(162)を有する端部(160)と
を含み、
ケーシング内に取り付けられたとき、前記第1側壁(44)における前記端部のエッジ(164)と前記ケーシングとの間において測定される間隔(D2)が、前記第2側壁(46)における前記端部のエッジ(166)と前記ケーシングとの間において測定される間隔(D1)よりも小さい
ことを特徴とする、ロータアセンブリにおいて使用されるエアフォイル(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(82)とを更に包含し、前記端部表面(162)が前記平面(82)に対して5°から15°の角度をなす、
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又は2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3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(82)とを更に包含し、前記端部表面(162)の前記平面(82)に対する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、
前記エアフォイル部分(42)の各々が、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(82)とを更に包含し、前記端部表面(162)の前記平面(82)に対する角度により、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、エアフォイル部分(42)を包含し、
該エアフォイル部分(42)の各々が、
凹状の第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、凸状の第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ように、前記第1の側壁に対して鋭角を形成し且つ前記第2の側壁に対して鈍角を形成するよう方向づけられた端部表面(162)を有する端部(160)と
を備え、
前記ロータアセンブリが前記タービン(10)のケーシング内に取り付けられたとき、
前記第1側壁(44)における前記端部のエッジ(164)と前記ケーシングとの間において測定される間隔(D2)が、前記第2側壁(46)における前記端部のエッジ(166)と前記ケーシングとの間において測定される間隔(D1)よりも小さい
ことを特徴とする、ロータアセンブリ。 - 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、
前記エアフォイル部分(42)の各々が、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(82)とを更に包含し、
前記端部表面(162)の前記平面(82)に対する角度により、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7記載のロータアセンブリ。 - 前記エアフォイル部分(42)の各々が、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(82)とを更に包含し、
前記端部表面(162)が前記平面(82)に対して5°から15°の角度をなす、
請求項7記載のロータアセンブリ。 - 前記エアフォイル部分(42)の各々が、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(82)とを更に包含し、
前記端部表面(162)の前記平面(82)に対する角度がレーキング処理により形成される、
請求項7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 | 2006-12-29 | ||
US11/617,911 US8172518B2 (en) | 2006-12-29 | 2006-12-29 | Methods and apparatus for fabricating a rotor assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008163949A JP2008163949A (ja) | 2008-07-17 |
JP5579965B2 true 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) |
Families Citing this family (12)
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 |
WO2011002570A1 (en) * | 2009-06-30 | 2011-01-06 | General Electric Company | Rotor blade and method for reducing tip rub loading |
US8662834B2 (en) * | 2009-06-30 | 2014-03-04 | General Electric Company | Method for reducing tip rub loading |
US8657570B2 (en) * | 2009-06-30 | 2014-02-25 | General Electric Company | Rotor blade with reduced 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 |
WO2014006467A2 (en) * | 2012-06-13 | 2014-01-09 | Pratt & Whitney Services Pte Ltd | Tip fabrication for rotor blade or stator vane airfoil |
GB2543327A (en) * | 2015-10-15 | 2017-04-19 | Rolls Royce Plc | Aerofoil tip profiles |
US10633983B2 (en) | 2016-03-07 | 2020-04-28 | General Electric Company | Airfoil tip geometry to reduce blade wear in gas turbine engines |
US10385865B2 (en) | 2016-03-07 | 2019-08-20 | 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 |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4274806A (en) | 1979-06-18 | 1981-06-23 | General Electric Company | Staircase blade tip |
US4390320A (en) * | 1980-05-01 | 1983-06-28 | General Electric Company | Tip cap for a rotor blade and method of replacement |
US4645417A (en) * | 1984-02-06 | 1987-02-24 | General Electric Company | Compressor casing recess |
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 |
US6234747B1 (en) * | 1999-11-15 | 2001-05-22 | General Electric Company | Rub resistant compressor stage |
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
Also Published As
Publication number | Publication date |
---|---|
CA2615625A1 (en) | 2008-06-29 |
EP1942252A3 (en) | 2010-11-03 |
EP1942252B1 (en) | 2014-04-02 |
CA2615625C (en) | 2015-12-01 |
JP2008163949A (ja) | 2008-07-17 |
US20080159869A1 (en) | 2008-07-03 |
EP1942252A2 (en) | 2008-07-09 |
US8172518B2 (en) | 2012-05-08 |
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