JPH10169403A5 - - Google Patents

Info

Publication number
JPH10169403A5
JPH10169403A5 JP1997347370A JP34737097A JPH10169403A5 JP H10169403 A5 JPH10169403 A5 JP H10169403A5 JP 1997347370 A JP1997347370 A JP 1997347370A JP 34737097 A JP34737097 A JP 34737097A JP H10169403 A5 JPH10169403 A5 JP H10169403A5
Authority
JP
Japan
Prior art keywords
web
trailing
stub shaft
rotor
stage
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.)
Pending
Application number
JP1997347370A
Other languages
English (en)
Other versions
JPH10169403A (ja
Filing date
Publication date
Priority claimed from US08/759,827 external-priority patent/US5735673A/en
Application filed filed Critical
Publication of JPH10169403A publication Critical patent/JPH10169403A/ja
Publication of JPH10169403A5 publication Critical patent/JPH10169403A5/ja
Pending legal-status Critical Current

Links

Description

後ウエブ７６は、内面９２と、後スプール取付け部材９４と、中央ハブ９６と、複数の第２のスタブシャフト９８とを包含する。後ウエブ７６の内面９２は、軸方向中心線２８に垂直な半径方向線１００に関して角度“λ”で形成されている。第２のスタブシャフト９８は、後ウエブ７６の周囲に分配されて、内面９２から外側へ延びている。各第２のスタブシャフト９８は、軸方向端１０２とウエブ端１０４との間に延びる。各第２のスタブシャフト９８のウエブ端１０４は、好適には、後ウエブ７６の内面９２に例えば金属結合により一体的に取付けられている。
【符号の説明】
１０ ガスタービンエンジン
１２ ファンセクション
１６ 案内ベーン
１８ 第１のロータ段
２０ 第１のステータ段
２２ 第２のロータ段
２４ 第２のステータ段
２６ 第３のロータ段
２８ 軸方向中心線
３０ スプール
３２ ロータディスク
３４ ロータブレードペア
３６ 第１のエアフォイル
３８ 第２のエアフォイル
４０ プラットフォーム
４２ 根元
４４ 前縁
４６ 後縁
４８ 外側半径方向表面
５０ 内側半径方向表面
５２ 第１の根元壁
５４ 第２の根元壁
５６ 中空部
５８ 基部
６０ 先端
６２ 前縁
６４ 後縁
６６ 前縁
６８ 後縁
７０ 相互ブレード領域
７２ 第１のファイバ
７３ 第２のファイバ
７４ 前ウエブ
７６ 後ウエブ
７８ 内面
８０ 前スプール取付け部材
８２ 前フランジ
８４ 中央ハブ
８６ 第１のスタブシャフト
８８ 軸方向端
９０ ウエブ端
９２ 内面
９４ 後スプール取付け部材
９６ 中央ハブ
９８ 第２のスタブシャフト
１００ 半径方向線
１０２ 軸方向端
１０４ ウエブ端
１０６ 締結具
１０８ フランジ
１１０ 外側半径方向表面
１１２ 組合せ面
１１４ タング

Claims (1)

  1. 請求項１２記載のロータブレードペアにおいて、前記ダンパが前記プラットフォームの相互ブレード領域から成り、この相互ブレード領域が前記第２のファイバを包含しているロータブレードペア。
JP9347370A 1996-12-04 1997-12-03 ロータブレードペア Pending JPH10169403A (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/759,827 1996-12-04
US08/759,827 US5735673A (en) 1996-12-04 1996-12-04 Turbine engine rotor blade pair

Publications (2)

Publication Number Publication Date
JPH10169403A JPH10169403A (ja) 1998-06-23
JPH10169403A5 true JPH10169403A5 (ja) 2005-07-21

Family

ID=25057108

Family Applications (1)

Application Number Title Priority Date Filing Date
JP9347370A Pending JPH10169403A (ja) 1996-12-04 1997-12-03 ロータブレードペア

Country Status (5)

Country Link
US (1) US5735673A (ja)
EP (1) EP0846845B1 (ja)
JP (1) JPH10169403A (ja)
KR (1) KR100497697B1 (ja)
DE (1) DE69734560T2 (ja)

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US6471474B1 (en) 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US7476086B2 (en) * 2005-04-07 2009-01-13 General Electric Company Tip cambered swept blade
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US7484935B2 (en) * 2005-06-02 2009-02-03 Honeywell International Inc. Turbine rotor hub contour
US7581924B2 (en) * 2006-07-27 2009-09-01 Siemens Energy, Inc. Turbine vanes with airfoil-proximate cooling seam
US7488157B2 (en) * 2006-07-27 2009-02-10 Siemens Energy, Inc. Turbine vane with removable platform inserts
JP4873200B2 (ja) * 2007-03-27 2012-02-08 株式会社Ｉｈｉ ファン動翼支持構造とこれを有するターボファンエンジン
US20080298973A1 (en) * 2007-05-29 2008-12-04 Siemens Power Generation, Inc. Turbine vane with divided turbine vane platform
US7887299B2 (en) * 2007-06-07 2011-02-15 Honeywell International Inc. Rotary body for turbo machinery with mistuned blades
US8366386B2 (en) * 2009-01-27 2013-02-05 United Technologies Corporation Method and assembly for gas turbine engine airfoils with protective coating
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US9279335B2 (en) 2011-08-03 2016-03-08 United Technologies Corporation Vane assembly for a gas turbine engine
US9273565B2 (en) 2012-02-22 2016-03-01 United Technologies Corporation Vane assembly for a gas turbine engine
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WO2015047445A2 (en) * 2013-03-05 2015-04-02 Freeman Ted J Composite gas turbine engine blade having multiple airfoils
WO2014163673A2 (en) 2013-03-11 2014-10-09 Bronwyn Power Gas turbine engine flow path geometry
JP2017530290A (ja) * 2014-08-22 2017-10-12 シーメンス エナジー インコーポレイテッド 別個のプラットフォーム支持システムを備えるモジュール式タービンブレード
US10458426B2 (en) 2016-09-15 2019-10-29 General Electric Company Aircraft fan with low part-span solidity
FR3074839B1 (fr) * 2017-12-13 2019-11-08 Safran Aircraft Engines Aube multipale de rotor de turbomachine et rotor la comprenant
US11339673B2 (en) 2020-01-17 2022-05-24 Raytheon Technologies Corporation Rotor assembly with internal vanes
US11434771B2 (en) * 2020-01-17 2022-09-06 Raytheon Technologies Corporation Rotor blade pair for rotational equipment
US11371351B2 (en) 2020-01-17 2022-06-28 Raytheon Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11208892B2 (en) * 2020-01-17 2021-12-28 Raytheon Technologies Corporation Rotor assembly with multiple rotor disks
US12116903B2 (en) 2021-06-30 2024-10-15 General Electric Company Composite airfoils with frangible tips
US12091984B2 (en) 2022-10-05 2024-09-17 General Electric Company Rotor assembly for a gas turbine engine
US12497893B2 (en) 2022-10-05 2025-12-16 General Electric Company Rotor assembly for a gas turbine engine
US12331661B2 (en) 2023-02-20 2025-06-17 General Electric Company Turbine engine with composite airfoils
US12345177B2 (en) 2023-02-20 2025-07-01 General Electric Company Turbine engine with composite airfoils
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