公开(公告)号：SG11201406230TA

公开(公告)日：2014-11-27

申请号：SG11201406230T

申请日：2013-04-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  SCHWARZ FREDERICK M

IPC: F02C3/067 ,  F02C3/107 ,  F02K3/072

公开(公告)号：SG11201404986TA

公开(公告)日：2014-11-27

申请号：SG11201404986T

申请日：2013-02-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F04B17/00

公开(公告)号：SG11201404962PA

公开(公告)日：2014-10-30

申请号：SG11201404962P

申请日：2013-02-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  SUCIU GABRIEL L

IPC: F02C3/067

Abstract: A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a low pressure turbine section and a high pressure turbine section. The low pressure compressor section, the low pressure turbine section and the fan rotate in a first direction whereas the high pressure compressor section and the high pressure turbine section rotate in a second direction opposite the first direction.

公开(公告)号：SG11201404761TA

公开(公告)日：2014-09-26

申请号：SG11201404761T

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D5/06 ,  F01D5/02 ,  F02C7/04

公开(公告)号：SG11201403008WA

公开(公告)日：2014-09-26

申请号：SG11201403008W

申请日：2012-12-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GLAHN JORN A ,  SCHWARZ FREDERICK M

IPC: F01D15/12

公开(公告)号：SG11201402663XA

公开(公告)日：2014-09-26

申请号：SG11201402663X

申请日：2013-01-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SMITH PETER G ,  OCHS STUART S ,  SCHWARZ FREDERICK M

IPC: F01D17/14

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation, and a gear system driven by a core engine within the core nacelle to drive a fan within the fan nacelle, the gear system defines a gear reduction ratio of greater than or equal to about 2.3.

公开(公告)号：SG11201403545SA

公开(公告)日：2014-07-30

申请号：SG11201403545S

申请日：2012-12-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOHLENBERG GREGORY A ,  ZAMORA SEAN P ,  SCHWARZ FREDERICK M

IPC: F01D25/24

公开(公告)号：CA2856723A1

公开(公告)日：2013-10-17

申请号：CA2856723

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  ACKERMANN WILLIAM K ,  KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/02

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

公开(公告)号：CA2854077A1

公开(公告)日：2013-08-08

申请号：CA2854077

申请日：2013-01-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL ,  ACKERMANN WILLIAM K ,  KUPRATIS DANIEL BERNARD

IPC: F04D29/04

Abstract: A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.

公开(公告)号：CA2853694A1

公开(公告)日：2013-07-18

申请号：CA2853694

申请日：2013-01-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SMITH PETER G ,  OCHS STUART S ,  SCHWARZ FREDERICK M

IPC: F01D17/14

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a core nacelle defined about an engine centerline axis, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path for a fan bypass airflow, a fan variable area nozzle axially movable relative the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation, and a gear system driven by a core engine within the core nacelle to drive a fan within the fan nacelle, the gear system defines a gear reduction ratio of greater than or equal to about 2.3.