STATOR ASSEMBLY WITH RETENTION CLIP FOR GAS TURBINE ENGINE

STATOR ASSEMBLY WITH RETENTION CLIP FOR GAS TURBINE ENGINE

A stator assembly (60) of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud (62) extending about an assembly axis (X) to bound a flow path (FP). The first shroud (62) defines a first shroud opening (68). An airfoil (66) has an airfoil...

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Hauptverfasser: BARAINCA, Brian, TREMBLAY, Dennis R, FEIGLESON, Steven J
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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creator BARAINCA, Brian
TREMBLAY, Dennis R
FEIGLESON, Steven J
description A stator assembly (60) of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud (62) extending about an assembly axis (X) to bound a flow path (FP). The first shroud (62) defines a first shroud opening (68). An airfoil (66) has an airfoil body (66A) extending from a first end portion (66B). The first end portion (66B) is received in the first shroud opening (68) and defines a pair of airfoil openings (66D). A retention clip (72) has an intermediate portion (72A) connecting a first leg portion (72B) and a second leg portion (72C). The intermediate portion (72A) is compressible to position the first and second leg portions (72B, 72C) in the pair of airfoil openings (66D) such that the retention clip (72) limits movement of the airfoil (66) relative to the first shroud (62).
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The first shroud (62) defines a first shroud opening (68). An airfoil (66) has an airfoil body (66A) extending from a first end portion (66B). The first end portion (66B) is received in the first shroud opening (68) and defines a pair of airfoil openings (66D). A retention clip (72) has an intermediate portion (72A) connecting a first leg portion (72B) and a second leg portion (72C). The intermediate portion (72A) is compressible to position the first and second leg portions (72B, 72C) in the pair of airfoil openings (66D) such that the retention clip (72) limits movement of the airfoil (66) relative to the first shroud (62).</description><language>eng ; fre ; ger</language><subject>BLASTING ; ENGINE PLANTS IN GENERAL ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2018</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20181128&amp;DB=EPODOC&amp;CC=EP&amp;NR=3406854A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20181128&amp;DB=EPODOC&amp;CC=EP&amp;NR=3406854A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BARAINCA, Brian</creatorcontrib><creatorcontrib>TREMBLAY, Dennis R</creatorcontrib><creatorcontrib>FEIGLESON, Steven J</creatorcontrib><title>STATOR ASSEMBLY WITH RETENTION CLIP FOR GAS TURBINE ENGINE</title><description>A stator assembly (60) of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud (62) extending about an assembly axis (X) to bound a flow path (FP). 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The first shroud (62) defines a first shroud opening (68). An airfoil (66) has an airfoil body (66A) extending from a first end portion (66B). The first end portion (66B) is received in the first shroud opening (68) and defines a pair of airfoil openings (66D). A retention clip (72) has an intermediate portion (72A) connecting a first leg portion (72B) and a second leg portion (72C). The intermediate portion (72A) is compressible to position the first and second leg portions (72B, 72C) in the pair of airfoil openings (66D) such that the retention clip (72) limits movement of the airfoil (66) relative to the first shroud (62).</abstract><oa>free_for_read</oa></addata></record>
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subjects BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
title STATOR ASSEMBLY WITH RETENTION CLIP FOR GAS TURBINE ENGINE
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