INTERNAL CORE PROFILE FOR A TURBINE NOZZLE AIRFOIL
An internal core profile for a first stage turbine nozzle airfoil of a gas turbine is provided to improve the aerodynamics and reduce the mechanical stress. A turbine nozzle substantially comprises an airfoil core having an uncoated nominal profile according to the Cartesian values of X, Y, and Z sh...
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| creator | JEFF GREENBERG DAVID DAY BARRY BROWN KIM JINUK KIM KWANGIL DARRYL ENG |
| description | An internal core profile for a first stage turbine nozzle airfoil of a gas turbine is provided to improve the aerodynamics and reduce the mechanical stress. A turbine nozzle substantially comprises an airfoil core having an uncoated nominal profile according to the Cartesian values of X, Y, and Z shown in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the X and Y coordinates define one of a plurality of airfoil profile sections at each Z distance when connected in a smooth continuous arc, and the plurality of airfoil profile sections define an airfoil shape when joined together in a smooth continuous arc.
가스 터빈의 제1 스테이지 터빈 노즐 에어포일을 위한 내부 코어 프로파일이 제공된다. 터빈 노즐은 실질적으로 표 1에 제시된 X, Y 및 Z의 직교 좌표값에 따라 코팅되지 않은 공칭 프로파일을 갖는 에어포일 코어를 포함하고, 상기 X, Y, Z 좌표는 직교 좌표계에서 측정된 인치 단위의 거리이며, 해당 X 및 Y 좌표는 부드러운 연속 호로 연결될 때 각 Z 거리에서 복수의 에어포일 코어 프로파일 섹션 중 하나를 정의하며, 상기 복수의 에어포일 코어 프로파일 섹션은 부드럽고 연속적인 호로 함께 결합될 때 에어포일 코어 형상을 정의한다. |
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가스 터빈의 제1 스테이지 터빈 노즐 에어포일을 위한 내부 코어 프로파일이 제공된다. 터빈 노즐은 실질적으로 표 1에 제시된 X, Y 및 Z의 직교 좌표값에 따라 코팅되지 않은 공칭 프로파일을 갖는 에어포일 코어를 포함하고, 상기 X, Y, Z 좌표는 직교 좌표계에서 측정된 인치 단위의 거리이며, 해당 X 및 Y 좌표는 부드러운 연속 호로 연결될 때 각 Z 거리에서 복수의 에어포일 코어 프로파일 섹션 중 하나를 정의하며, 상기 복수의 에어포일 코어 프로파일 섹션은 부드럽고 연속적인 호로 함께 결합될 때 에어포일 코어 형상을 정의한다.</description><language>eng ; kor</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>2023</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&date=20230126&DB=EPODOC&CC=KR&NR=20230012957A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20230126&DB=EPODOC&CC=KR&NR=20230012957A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>JEFF GREENBERG</creatorcontrib><creatorcontrib>DAVID DAY</creatorcontrib><creatorcontrib>BARRY BROWN</creatorcontrib><creatorcontrib>KIM JINUK</creatorcontrib><creatorcontrib>KIM KWANGIL</creatorcontrib><creatorcontrib>DARRYL ENG</creatorcontrib><title>INTERNAL CORE PROFILE FOR A TURBINE NOZZLE AIRFOIL</title><description>An internal core profile for a first stage turbine nozzle airfoil of a gas turbine is provided to improve the aerodynamics and reduce the mechanical stress. A turbine nozzle substantially comprises an airfoil core having an uncoated nominal profile according to the Cartesian values of X, Y, and Z shown in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the X and Y coordinates define one of a plurality of airfoil profile sections at each Z distance when connected in a smooth continuous arc, and the plurality of airfoil profile sections define an airfoil shape when joined together in a smooth continuous arc.
가스 터빈의 제1 스테이지 터빈 노즐 에어포일을 위한 내부 코어 프로파일이 제공된다. 터빈 노즐은 실질적으로 표 1에 제시된 X, Y 및 Z의 직교 좌표값에 따라 코팅되지 않은 공칭 프로파일을 갖는 에어포일 코어를 포함하고, 상기 X, Y, Z 좌표는 직교 좌표계에서 측정된 인치 단위의 거리이며, 해당 X 및 Y 좌표는 부드러운 연속 호로 연결될 때 각 Z 거리에서 복수의 에어포일 코어 프로파일 섹션 중 하나를 정의하며, 상기 복수의 에어포일 코어 프로파일 섹션은 부드럽고 연속적인 호로 함께 결합될 때 에어포일 코어 형상을 정의한다.</description><subject>BLASTING</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDDy9AtxDfJz9FFw9g9yVQgI8nfz9HFVcPMPUnBUCAkNcvL0c1Xw84-KAgo6ega5-Xv68DCwpiXmFKfyQmluBmU31xBnD93Ugvz41OKCxOTUvNSSeO8gIwMjYwMDQyNLU3NHY-JUAQAGcyeT</recordid><startdate>20230126</startdate><enddate>20230126</enddate><creator>JEFF GREENBERG</creator><creator>DAVID DAY</creator><creator>BARRY BROWN</creator><creator>KIM JINUK</creator><creator>KIM KWANGIL</creator><creator>DARRYL ENG</creator><scope>EVB</scope></search><sort><creationdate>20230126</creationdate><title>INTERNAL CORE PROFILE FOR A TURBINE NOZZLE AIRFOIL</title><author>JEFF GREENBERG ; DAVID DAY ; BARRY BROWN ; KIM JINUK ; KIM KWANGIL ; DARRYL ENG</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_KR20230012957A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; kor</language><creationdate>2023</creationdate><topic>BLASTING</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>JEFF GREENBERG</creatorcontrib><creatorcontrib>DAVID DAY</creatorcontrib><creatorcontrib>BARRY BROWN</creatorcontrib><creatorcontrib>KIM JINUK</creatorcontrib><creatorcontrib>KIM KWANGIL</creatorcontrib><creatorcontrib>DARRYL ENG</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>JEFF GREENBERG</au><au>DAVID DAY</au><au>BARRY BROWN</au><au>KIM JINUK</au><au>KIM KWANGIL</au><au>DARRYL ENG</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>INTERNAL CORE PROFILE FOR A TURBINE NOZZLE AIRFOIL</title><date>2023-01-26</date><risdate>2023</risdate><abstract>An internal core profile for a first stage turbine nozzle airfoil of a gas turbine is provided to improve the aerodynamics and reduce the mechanical stress. A turbine nozzle substantially comprises an airfoil core having an uncoated nominal profile according to the Cartesian values of X, Y, and Z shown in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the X and Y coordinates define one of a plurality of airfoil profile sections at each Z distance when connected in a smooth continuous arc, and the plurality of airfoil profile sections define an airfoil shape when joined together in a smooth continuous arc.
가스 터빈의 제1 스테이지 터빈 노즐 에어포일을 위한 내부 코어 프로파일이 제공된다. 터빈 노즐은 실질적으로 표 1에 제시된 X, Y 및 Z의 직교 좌표값에 따라 코팅되지 않은 공칭 프로파일을 갖는 에어포일 코어를 포함하고, 상기 X, Y, Z 좌표는 직교 좌표계에서 측정된 인치 단위의 거리이며, 해당 X 및 Y 좌표는 부드러운 연속 호로 연결될 때 각 Z 거리에서 복수의 에어포일 코어 프로파일 섹션 중 하나를 정의하며, 상기 복수의 에어포일 코어 프로파일 섹션은 부드럽고 연속적인 호로 함께 결합될 때 에어포일 코어 형상을 정의한다.</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 | INTERNAL CORE PROFILE FOR A TURBINE NOZZLE AIRFOIL |
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