-
公开(公告)号：BR102013001737A2
公开(公告)日：2015-05-12
申请号：BR102013001737
申请日：2013-01-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D
Abstract: Motor de turbina a gás. É descrito um motor de turbina a gás que inclui um eixo definindo um eixo geométrico de rotação. Um rotor da turbina externa aciona diretamente o eixo e inclui um conjunto externo de pás. Um rotor da turbina interna tem um conjunto interno de pás entremeado com o conjunto externo de pás. O rotor da turbina interna é configurado para girar em uma direção oposta em torno do eixo geométrico de rotação em relação ao rotor da turbina externa. Um sistema de engrenagem acopla o rotor da turbina interna no eixo e é configurado para girar o conjunto interno de pás a uma maior velocidade que o conjunto externo de pás. O sistema de engrenagem é montado em uma armação da turbina intermediária
-
公开(公告)号：CA2805279A1
公开(公告)日：2013-08-29
申请号：CA2805279
申请日：2013-02-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D
Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. The gear system is mounted to a mid-turbine frame.
-
公开(公告)号：DE60220875D1
公开(公告)日：2007-08-09
申请号：DE60220875
申请日：2002-12-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MERRY BRIAN D
IPC: F01D5/18
Abstract: A coolable rotor blade (42) having an airfoil (64) having two serpentine passages (122,124), is disclosed. Various construction details are developed for providing cooling to the leading edge (68) region and the trailing edge region (74) of the airfoil. In one detailed embodiment, the airfoil trip strips (T) in the passages having constant height e and constant pitch e/p over each leg in most legs of the passages except for the legs closest to the edge regions of the airfoil.
-
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.
-
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.
-
Patent Agency Ranking
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.
-
公开(公告)号：CA2800001A1
公开(公告)日：2013-06-30
申请号：CA2800001
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, said spool includes a low pressure compressor with four to eight (4-8) stages.
-
公开(公告)号：DE60220875T2
公开(公告)日：2008-02-28
申请号：DE60220875
申请日：2002-12-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MERRY BRIAN D
IPC: F01D5/18
Abstract: A coolable rotor blade (42) having an airfoil (64) having two serpentine passages (122,124), is disclosed. Various construction details are developed for providing cooling to the leading edge (68) region and the trailing edge region (74) of the airfoil. In one detailed embodiment, the airfoil trip strips (T) in the passages having constant height e and constant pitch e/p over each leg in most legs of the passages except for the legs closest to the edge regions of the airfoil.
-
公开(公告)号：CA2800001C
公开(公告)日：2015-10-13
申请号：CA2800001
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, said spool includes a low pressure compressor with four to eight (4-8) stages.
-
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.
-
-
-
-
-
-
-
-
-
Search Results
81
records
(took 0.024 seconds)
