JP2002195103A5 - - Google Patents

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Publication number
JP2002195103A5
JP2002195103A5 JP2001360414A JP2001360414A JP2002195103A5 JP 2002195103 A5 JP2002195103 A5 JP 2002195103A5 JP 2001360414 A JP2001360414 A JP 2001360414A JP 2001360414 A JP2001360414 A JP 2001360414A JP 2002195103 A5 JP2002195103 A5 JP 2002195103A5
Authority
JP
Japan
Prior art keywords
dovetail
land portion
spacer
slot
backbone
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
Application number
JP2001360414A
Other languages
English (en)
Japanese (ja)
Other versions
JP4052375B2 (ja
JP2002195103A (ja
Filing date
Publication date
Priority claimed from US09/723,110 external-priority patent/US6481971B1/en
Application filed filed Critical
Publication of JP2002195103A publication Critical patent/JP2002195103A/ja
Publication of JP2002195103A5 publication Critical patent/JP2002195103A5/ja
Application granted granted Critical
Publication of JP4052375B2 publication Critical patent/JP4052375B2/ja
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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JP2001360414A 2000-11-27 2001-11-27 ブレード・スペーサ Expired - Fee Related JP4052375B2 (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US09/723,110 US6481971B1 (en) 2000-11-27 2000-11-27 Blade spacer
US09/723110 2000-11-27

Publications (3)

Publication Number Publication Date
JP2002195103A JP2002195103A (ja) 2002-07-10
JP2002195103A5 true JP2002195103A5 (enExample) 2005-05-19
JP4052375B2 JP4052375B2 (ja) 2008-02-27

Family

ID=24904888

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2001360414A Expired - Fee Related JP4052375B2 (ja) 2000-11-27 2001-11-27 ブレード・スペーサ

Country Status (6)

Country Link
US (1) US6481971B1 (enExample)
EP (1) EP1209322B1 (enExample)
JP (1) JP4052375B2 (enExample)
DE (1) DE60118315T2 (enExample)
PL (1) PL200997B1 (enExample)
RU (1) RU2281403C2 (enExample)

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US8961141B2 (en) 2011-08-29 2015-02-24 United Technologies Corporation Axial retention system for a bladed rotor with multiple blade types
US8851854B2 (en) 2011-12-16 2014-10-07 United Technologies Corporation Energy absorbent fan blade spacer
CN102588002A (zh) * 2012-03-15 2012-07-18 北京航空航天大学 一种低应力圆弧面圆弧榫连接结构
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
EP2885506B8 (en) 2012-08-17 2021-03-31 Raytheon Technologies Corporation Contoured flowpath surface
US9376926B2 (en) 2012-11-15 2016-06-28 United Technologies Corporation Gas turbine engine fan blade lock assembly
US9359906B2 (en) 2012-12-18 2016-06-07 United Technologies Corporation Rotor blade root spacer with a fracture feature
US9422819B2 (en) 2012-12-18 2016-08-23 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
WO2014105104A1 (en) * 2012-12-27 2014-07-03 United Technologies Corporation Blade underroot spacer with hook removal
WO2014113009A1 (en) 2013-01-17 2014-07-24 United Technologies Corporation Rotor blade root spacer with grip element
US9297257B2 (en) * 2013-01-31 2016-03-29 General Electric Company Spinner assembly with removable fan blade leading edge fairings
CN103985407A (zh) 2013-02-07 2014-08-13 辉达公司 采用分段式页面配置的dram
US9759226B2 (en) 2013-02-15 2017-09-12 United Technologies Corporation Low profile fan platform attachment
EP2964522B1 (en) 2013-03-06 2021-06-16 Raytheon Technologies Corporation Gas turbine engine nose cone attachment
WO2014143268A1 (en) * 2013-03-12 2014-09-18 United Technologies Corporation T-shaped platform leading edge anti-rotation tabs
RU2525376C1 (ru) * 2013-03-28 2014-08-10 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Рабочее колесо осевого компрессора газотурбинного двигателя
WO2015073096A2 (en) * 2013-09-13 2015-05-21 United Technologies Corporation Fan platform
US10392951B2 (en) 2014-10-02 2019-08-27 United Technologies Corporation Vane assembly with trapped segmented vane structures
FR3038653B1 (fr) * 2015-07-08 2017-08-04 Snecma Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante
US9976426B2 (en) * 2015-07-21 2018-05-22 United Technologies Corporation Fan platform with stiffening feature
ES2733952T3 (es) * 2015-12-15 2019-12-03 MTU Aero Engines AG Estructura de fijación
FR3048997B1 (fr) * 2016-03-21 2020-03-27 Safran Aircraft Engines Plateforme d'aube et disque de soufflante de turbomachine aeronautique
US11174741B2 (en) 2018-04-19 2021-11-16 Raytheon Technologies Corporation Platform for an airfoil of a gas turbine engine
US11339674B2 (en) * 2018-08-14 2022-05-24 Rolls-Royce North American Technologies Inc. Blade retainer for gas turbine engine
US11168572B2 (en) * 2019-02-05 2021-11-09 Raytheon Technologies Corporation Composite gas turbine engine component
FR3107724B1 (fr) * 2020-02-27 2022-06-24 Safran Aircraft Engines Rotor de soufflante à aubes à calage variable et turbomachine équipée d’un tel rotor
US11834964B2 (en) 2021-11-24 2023-12-05 General Electric Company Low radius ratio fan blade for a gas turbine engine
IT202100029963A1 (it) * 2021-11-26 2023-05-26 Ge Avio Srl Motore a turbina a gas comprendente un complesso di pale rotanti.
US12692874B2 (en) 2022-11-14 2026-07-28 General Electric Company Turbomachine and method of assembly
US12663016B2 (en) 2022-11-14 2026-06-23 General Electric Company Turbomachine and method of assembly
US12674467B2 (en) 2022-11-14 2026-07-07 General Electric Company Turbomachine and method of assembly
US11852161B1 (en) 2022-11-14 2023-12-26 General Electric Company Turbomachine and method of assembly
US12674468B2 (en) 2022-11-14 2026-07-07 General Electric Company Turbomachine and method of assembly
US12680552B2 (en) 2022-11-14 2026-07-14 General Electric Company Turbomachine and method of assembly

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JPH04259601A (ja) * 1991-02-12 1992-09-16 Toshiba Corp タービン動翼植込構造
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US5281096A (en) 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
US5282720A (en) 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
US5350279A (en) 1993-07-02 1994-09-27 General Electric Company Gas turbine engine blade retainer sub-assembly
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US6033185A (en) 1998-09-28 2000-03-07 General Electric Company Stress relieved dovetail

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