Aero-engine turbine blade surface crystal temperature measurement correction method
The invention belongs to the technical field of aero-engine turbine blade surface crystal temperature measurement, and particularly relates to an aero-engine turbine blade surface crystal temperature measurement correction method, which comprises the steps of 1, acquiring a distance L from a crystal...
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| creator | TAO YILUAN LIU TAIQIU WEI WENTAO QU YUNFENG QIU DANDAN |
| description | The invention belongs to the technical field of aero-engine turbine blade surface crystal temperature measurement, and particularly relates to an aero-engine turbine blade surface crystal temperature measurement correction method, which comprises the steps of 1, acquiring a distance L from a crystal to the outer wall surface of a turbine blade; 2, the temperature tm of the position, L away from the outer wall face, in the turbine blade is measured, and the crystal measurement temperature tjt is taken; 3, calculating the heat flux q between the gas side and the cold air side of the turbine blade; 4, based on tm and q, the temperature tb of the outer wall face of the turbine blade is calculated; and 5, based on tb and q, calculating the temperature ttc of the outer wall surface of the turbine blade coating.
本申请属于航空发动机涡轮叶片表面晶体测温技术领域，具体涉及一种航空发动机涡轮叶片表面晶体测温修正方法，包括：步骤一、获取晶体到涡轮叶片外壁面的距离L；步骤二、将涡轮叶片内部距离外壁面L处的温度tm，取晶体测量温度tjt；步骤三、计算涡轮叶片燃气侧、冷气侧间的热通量q；步骤四、基于tm、q，计算涡轮叶片外壁面温度tb；步骤五、基于tb、q，计算涡轮叶片涂层外壁面温度ttc。 |
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本申请属于航空发动机涡轮叶片表面晶体测温技术领域，具体涉及一种航空发动机涡轮叶片表面晶体测温修正方法，包括：步骤一、获取晶体到涡轮叶片外壁面的距离L；步骤二、将涡轮叶片内部距离外壁面L处的温度tm，取晶体测量温度tjt；步骤三、计算涡轮叶片燃气侧、冷气侧间的热通量q；步骤四、基于tm、q，计算涡轮叶片外壁面温度tb；步骤五、基于tb、q，计算涡轮叶片涂层外壁面温度ttc。</description><language>chi ; eng</language><subject>MEASURING ; MEASURING QUANTITY OF HEAT ; MEASURING TEMPERATURE ; PHYSICS ; TESTING ; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR</subject><creationdate>2024</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=20240702&DB=EPODOC&CC=CN&NR=118275002A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20240702&DB=EPODOC&CC=CN&NR=118275002A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>TAO YILUAN</creatorcontrib><creatorcontrib>LIU TAIQIU</creatorcontrib><creatorcontrib>WEI WENTAO</creatorcontrib><creatorcontrib>QU YUNFENG</creatorcontrib><creatorcontrib>QIU DANDAN</creatorcontrib><title>Aero-engine turbine blade surface crystal temperature measurement correction method</title><description>The invention belongs to the technical field of aero-engine turbine blade surface crystal temperature measurement, and particularly relates to an aero-engine turbine blade surface crystal temperature measurement correction method, which comprises the steps of 1, acquiring a distance L from a crystal to the outer wall surface of a turbine blade; 2, the temperature tm of the position, L away from the outer wall face, in the turbine blade is measured, and the crystal measurement temperature tjt is taken; 3, calculating the heat flux q between the gas side and the cold air side of the turbine blade; 4, based on tm and q, the temperature tb of the outer wall face of the turbine blade is calculated; and 5, based on tb and q, calculating the temperature ttc of the outer wall surface of the turbine blade coating.
本申请属于航空发动机涡轮叶片表面晶体测温技术领域，具体涉及一种航空发动机涡轮叶片表面晶体测温修正方法，包括：步骤一、获取晶体到涡轮叶片外壁面的距离L；步骤二、将涡轮叶片内部距离外壁面L处的温度tm，取晶体测量温度tjt；步骤三、计算涡轮叶片燃气侧、冷气侧间的热通量q；步骤四、基于tm、q，计算涡轮叶片外壁面温度tb；步骤五、基于tb、q，计算涡轮叶片涂层外壁面温度ttc。</description><subject>MEASURING</subject><subject>MEASURING QUANTITY OF HEAT</subject><subject>MEASURING TEMPERATURE</subject><subject>PHYSICS</subject><subject>TESTING</subject><subject>THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2024</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNjDsKwkAURaexEHUPzwUEkohoG4JiZaN9mExuYmB-vHkp3L0juACrA-ce7lo9GnAo4KfZg2Th_sve6gGUFh61ARl-J9GWBC6CdY5ADjrPcPBCJjDDyBx81vIKw1atRm0Tdj9u1P56eba3AjF0SDGfekjX3qvqXJ-OZVk3h3-aD7ZPOUE</recordid><startdate>20240702</startdate><enddate>20240702</enddate><creator>TAO YILUAN</creator><creator>LIU TAIQIU</creator><creator>WEI WENTAO</creator><creator>QU YUNFENG</creator><creator>QIU DANDAN</creator><scope>EVB</scope></search><sort><creationdate>20240702</creationdate><title>Aero-engine turbine blade surface crystal temperature measurement correction method</title><author>TAO YILUAN ; LIU TAIQIU ; WEI WENTAO ; QU YUNFENG ; QIU DANDAN</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN118275002A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2024</creationdate><topic>MEASURING</topic><topic>MEASURING QUANTITY OF HEAT</topic><topic>MEASURING TEMPERATURE</topic><topic>PHYSICS</topic><topic>TESTING</topic><topic>THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR</topic><toplevel>online_resources</toplevel><creatorcontrib>TAO YILUAN</creatorcontrib><creatorcontrib>LIU TAIQIU</creatorcontrib><creatorcontrib>WEI WENTAO</creatorcontrib><creatorcontrib>QU YUNFENG</creatorcontrib><creatorcontrib>QIU DANDAN</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>TAO YILUAN</au><au>LIU TAIQIU</au><au>WEI WENTAO</au><au>QU YUNFENG</au><au>QIU DANDAN</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Aero-engine turbine blade surface crystal temperature measurement correction method</title><date>2024-07-02</date><risdate>2024</risdate><abstract>The invention belongs to the technical field of aero-engine turbine blade surface crystal temperature measurement, and particularly relates to an aero-engine turbine blade surface crystal temperature measurement correction method, which comprises the steps of 1, acquiring a distance L from a crystal to the outer wall surface of a turbine blade; 2, the temperature tm of the position, L away from the outer wall face, in the turbine blade is measured, and the crystal measurement temperature tjt is taken; 3, calculating the heat flux q between the gas side and the cold air side of the turbine blade; 4, based on tm and q, the temperature tb of the outer wall face of the turbine blade is calculated; and 5, based on tb and q, calculating the temperature ttc of the outer wall surface of the turbine blade coating.
本申请属于航空发动机涡轮叶片表面晶体测温技术领域，具体涉及一种航空发动机涡轮叶片表面晶体测温修正方法，包括：步骤一、获取晶体到涡轮叶片外壁面的距离L；步骤二、将涡轮叶片内部距离外壁面L处的温度tm，取晶体测量温度tjt；步骤三、计算涡轮叶片燃气侧、冷气侧间的热通量q；步骤四、基于tm、q，计算涡轮叶片外壁面温度tb；步骤五、基于tb、q，计算涡轮叶片涂层外壁面温度ttc。</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | MEASURING MEASURING QUANTITY OF HEAT MEASURING TEMPERATURE PHYSICS TESTING THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR |
| title | Aero-engine turbine blade surface crystal temperature measurement correction method |
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