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公开(公告)号：CA2800464C
公开(公告)日：2015-04-07
申请号：CA2800464
申请日：2012-12-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
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公开(公告)号：CA2850225C
公开(公告)日：2015-10-13
申请号：CA2850225
申请日：2012-12-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HASEL KARL L , STAUBACH JOSEPH B , MERRY BRIAN D , SUCIU GABRIEL L , DYE CHRISTOPHER M
Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.
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公开(公告)号：SG11201407138QA
公开(公告)日：2015-01-29
申请号：SG11201407138Q
申请日：2013-04-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , SNAPE NATHAN , DYE CHRISTOPHER M
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公开(公告)号：CA2849013C
公开(公告)日：2014-11-18
申请号：CA2849013
申请日：2012-12-31
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine centeriine axis which drives the gear train, the spool includes a low stage count low pressure turbine. In a further non-limiting embodiment of any of the foregoing gas turbine engine embodiments, the low stage count may include three to six (3-6) stages. Additionally or alternatively, the low stage count may include three (3) stages. Additionally or alternatively, the low stage count may include five (5) or six (6) stages.
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公开(公告)号：PL2788602T3
公开(公告)日：2018-06-29
申请号：PL12869230
申请日：2012-12-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DUONG HUNG , SUCIU GABRIEL L , DYE CHRISTOPHER M
IPC: F02C7/32
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Patent Agency Ranking
公开(公告)号：BR102012028942A2
公开(公告)日：2016-11-01
申请号：BR102012028942
申请日：2012-11-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MERRY BRIAN D , DYE CHRISTOPHER M , SCHWARZ FREDERICK M , SUCIU GABRIEL L , JOHNSON STEVEN B
Abstract: motor de turbina a gás. a presente inven$o se refere a um motor de turbina a gás que inclui um eixo do conjunto compressor-turbina ao longo de um eixo da linha e centro do motor que aciona um trem de engrenagem.
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公开(公告)号：RU2687861C9
公开(公告)日：2019-08-01
申请号：RU2014131372
申请日：2012-12-31
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRI BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: Газотурбинныйдвигательсодержитредуктор, расположенныйвдольпродольнойосидвигателя, каскад, гондолувентилятора, внутреннююгондолу, вентилятор, вентиляторноесоплои внутреннийконтур. Каскадвыполненс возможностьюприведенияв действиередуктораи содержиттурбинунизкогодавленияс числомступенейоттрехдошести. Гондолавентилятораустановленавокругвнутреннейгондолыи определяеттрактдлявоздушногопотоканаружногоконтуравентилятора, причемстепеньдвухконтурностипревышаетшесть. Вентиляторноесопловыполненос изменяемойплощадьюсеченияи свозможностьюперемещенияв осевомнаправленииотносительногондолывентиляторас цельюизмененияплощадивыходногосечениявентиляторногосоплаи регулированиявоздушногопотокав наружномконтуревентиляторавовремяработыдвигателя. Вентиляторвыполненс возможностьювращениясоскоростьювентиляторавокругпродольнойосии приводитсяв действиетурбинойнизкогодавленияс помощьюредуктора, причемскоростьвентилятораменьшескороститурбинынизкогодавления. Внутреннийконтурокруженвнутреннейгондолой. Редукторимеетпередаточноеотношение, котороебольшеилиравно 2,3, причемминимальноесоотношениедавленийв вентиляторесоставляетменее 1,45, аминимальнаяприведеннаяокружнаяскоростьлопаткивентиляторасоставляетменее 1150 фут/сек (350,5 м/сек). Изобретениепозволяетобеспечитьболеелегкуюконструкциюгазотурбинногодвигателя, атакжеснизитьшум, производимыйвентилятором. 12 з.п. ф-лы, 15 ил.
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公开(公告)号：CA2850225A1
公开(公告)日：2013-07-04
申请号：CA2850225
申请日：2012-12-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： HASEL KARL L , STAUBACH JOSEPH B , MERRY BRIAN D , SUCIU GABRIEL L , DYE CHRISTOPHER M
IPC: F01D1/04
Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.
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公开(公告)号：CA2849013A1
公开(公告)日：2013-07-04
申请号：CA2849013
申请日：2012-12-31
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine centeriine axis which drives the gear train, the spool includes a low stage count low pressure turbine. In a further non-limiting embodiment of any of the foregoing gas turbine engine embodiments, the low stage count may include three to six (3-6) stages. Additionally or alternatively, the low stage count may include three (3) stages. Additionally or alternatively, the low stage count may include five (5) or six (6) stages.
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公开(公告)号：CA2800464A1
公开(公告)日：2013-06-30
申请号：CA2800464
申请日：2012-12-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
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