COOLED AIRFOIL, GUIDE VANE, AND METHOD OF MANUFACTURING AIRFOIL AND GUIDE VANE
PROBLEM TO BE SOLVED: To provide an airfoil having a first airfoil height section extending toward a tip, in which, in a meridional view, a leading edge and a trailing edge are straight along the first airfoil height section, the airfoil has a second airfoil height section adjacent to the tip and ex...
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| creator | FRANK GERSBACH WARDLE BRIAN KENNETH IANNIS BUFFART |
| description | PROBLEM TO BE SOLVED: To provide an airfoil having a first airfoil height section extending toward a tip, in which, in a meridional view, a leading edge and a trailing edge are straight along the first airfoil height section, the airfoil has a second airfoil height section adjacent to the tip and extending toward a hub end, the airfoil is concavely shaped at the leading edge, and convexly shaped at the trailing edge along the second airfoil height section.SOLUTION: At least one cooling channel (65, 66, 67) is provided within an airfoil (61), and the cooling channel is extended straight in a first cooling channel length section, and is bent in a second cooling channel length section. A cooling channel wall provided on a leading edge (LE) side is convexly shaped and a cooling channel wall provided on a trailing edge (TE) side is concavely shaped. Moreover, a method for casting the airfoil is disclosed.SELECTED DRAWING: Figure 2
【課題】翼は、先端部に向かって延びる第１の翼高さセクションを有し、メリジオナル図において、前縁と後縁とは、第１の翼高さセクションに沿って直線的であり、翼は、先端部に隣接した、ハブ端部に向かって延びる第２の翼高さセクションを有し、翼は、前縁において凹面状の形状を有しており、かつ第２の翼高さセクションに沿って後縁において凸面状の形状を有する。【解決手段】少なくとも１つの冷却通路（６５，６６，６７）が、翼（６１）内に設けられており、冷却通路は第１の冷却通路長さセクションにおいて直線的に延びており、かつ第２の冷却通路長さセクションにおいて曲がっており、前縁（ＬＥ）側に設けられた冷却通路壁は、凸面の形状を有し、後縁（ＴＥ）側に設けられた冷却通路壁は、凹面の形状を有する。さらに、翼を鋳造する方法が開示されている。【選択図】図２ |
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【課題】翼は、先端部に向かって延びる第１の翼高さセクションを有し、メリジオナル図において、前縁と後縁とは、第１の翼高さセクションに沿って直線的であり、翼は、先端部に隣接した、ハブ端部に向かって延びる第２の翼高さセクションを有し、翼は、前縁において凹面状の形状を有しており、かつ第２の翼高さセクションに沿って後縁において凸面状の形状を有する。【解決手段】少なくとも１つの冷却通路（６５，６６，６７）が、翼（６１）内に設けられており、冷却通路は第１の冷却通路長さセクションにおいて直線的に延びており、かつ第２の冷却通路長さセクションにおいて曲がっており、前縁（ＬＥ）側に設けられた冷却通路壁は、凸面の形状を有し、後縁（ＴＥ）側に設けられた冷却通路壁は、凹面の形状を有する。さらに、翼を鋳造する方法が開示されている。【選択図】図２</description><language>eng ; jpn</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>2017</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=20170126&DB=EPODOC&CC=JP&NR=2017020490A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25544,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20170126&DB=EPODOC&CC=JP&NR=2017020490A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>FRANK GERSBACH</creatorcontrib><creatorcontrib>WARDLE BRIAN KENNETH</creatorcontrib><creatorcontrib>IANNIS BUFFART</creatorcontrib><title>COOLED AIRFOIL, GUIDE VANE, AND METHOD OF MANUFACTURING AIRFOIL AND GUIDE VANE</title><description>PROBLEM TO BE SOLVED: To provide an airfoil having a first airfoil height section extending toward a tip, in which, in a meridional view, a leading edge and a trailing edge are straight along the first airfoil height section, the airfoil has a second airfoil height section adjacent to the tip and extending toward a hub end, the airfoil is concavely shaped at the leading edge, and convexly shaped at the trailing edge along the second airfoil height section.SOLUTION: At least one cooling channel (65, 66, 67) is provided within an airfoil (61), and the cooling channel is extended straight in a first cooling channel length section, and is bent in a second cooling channel length section. A cooling channel wall provided on a leading edge (LE) side is convexly shaped and a cooling channel wall provided on a trailing edge (TE) side is concavely shaped. Moreover, a method for casting the airfoil is disclosed.SELECTED DRAWING: Figure 2
【課題】翼は、先端部に向かって延びる第１の翼高さセクションを有し、メリジオナル図において、前縁と後縁とは、第１の翼高さセクションに沿って直線的であり、翼は、先端部に隣接した、ハブ端部に向かって延びる第２の翼高さセクションを有し、翼は、前縁において凹面状の形状を有しており、かつ第２の翼高さセクションに沿って後縁において凸面状の形状を有する。【解決手段】少なくとも１つの冷却通路（６５，６６，６７）が、翼（６１）内に設けられており、冷却通路は第１の冷却通路長さセクションにおいて直線的に延びており、かつ第２の冷却通路長さセクションにおいて曲がっており、前縁（ＬＥ）側に設けられた冷却通路壁は、凸面の形状を有し、後縁（ＴＥ）側に設けられた冷却通路壁は、凹面の形状を有する。さらに、翼を鋳造する方法が開示されている。【選択図】図２</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>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZPBz9vf3cXVRcPQMcvP39NFRcA_1dHFVCHP0c9VRcPRzUfB1DfHwd1Hwd1PwdfQLdXN0DgkN8vRzh2kAq0Ho4WFgTUvMKU7lhdLcDEpuriHOHrqpBfnxqcUFicmpeakl8V4BRgaG5gZGBiaWBo7GRCkCAAZuLhU</recordid><startdate>20170126</startdate><enddate>20170126</enddate><creator>FRANK GERSBACH</creator><creator>WARDLE BRIAN KENNETH</creator><creator>IANNIS BUFFART</creator><scope>EVB</scope></search><sort><creationdate>20170126</creationdate><title>COOLED AIRFOIL, GUIDE VANE, AND METHOD OF MANUFACTURING AIRFOIL AND GUIDE VANE</title><author>FRANK GERSBACH ; WARDLE BRIAN KENNETH ; IANNIS BUFFART</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2017020490A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; jpn</language><creationdate>2017</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>FRANK GERSBACH</creatorcontrib><creatorcontrib>WARDLE BRIAN KENNETH</creatorcontrib><creatorcontrib>IANNIS BUFFART</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>FRANK GERSBACH</au><au>WARDLE BRIAN KENNETH</au><au>IANNIS BUFFART</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>COOLED AIRFOIL, GUIDE VANE, AND METHOD OF MANUFACTURING AIRFOIL AND GUIDE VANE</title><date>2017-01-26</date><risdate>2017</risdate><abstract>PROBLEM TO BE SOLVED: To provide an airfoil having a first airfoil height section extending toward a tip, in which, in a meridional view, a leading edge and a trailing edge are straight along the first airfoil height section, the airfoil has a second airfoil height section adjacent to the tip and extending toward a hub end, the airfoil is concavely shaped at the leading edge, and convexly shaped at the trailing edge along the second airfoil height section.SOLUTION: At least one cooling channel (65, 66, 67) is provided within an airfoil (61), and the cooling channel is extended straight in a first cooling channel length section, and is bent in a second cooling channel length section. A cooling channel wall provided on a leading edge (LE) side is convexly shaped and a cooling channel wall provided on a trailing edge (TE) side is concavely shaped. Moreover, a method for casting the airfoil is disclosed.SELECTED DRAWING: Figure 2
【課題】翼は、先端部に向かって延びる第１の翼高さセクションを有し、メリジオナル図において、前縁と後縁とは、第１の翼高さセクションに沿って直線的であり、翼は、先端部に隣接した、ハブ端部に向かって延びる第２の翼高さセクションを有し、翼は、前縁において凹面状の形状を有しており、かつ第２の翼高さセクションに沿って後縁において凸面状の形状を有する。【解決手段】少なくとも１つの冷却通路（６５，６６，６７）が、翼（６１）内に設けられており、冷却通路は第１の冷却通路長さセクションにおいて直線的に延びており、かつ第２の冷却通路長さセクションにおいて曲がっており、前縁（ＬＥ）側に設けられた冷却通路壁は、凸面の形状を有し、後縁（ＴＥ）側に設けられた冷却通路壁は、凹面の形状を有する。さらに、翼を鋳造する方法が開示されている。【選択図】図２</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 | COOLED AIRFOIL, GUIDE VANE, AND METHOD OF MANUFACTURING AIRFOIL AND GUIDE VANE |
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