公开(公告)号：CA2889618A1

公开(公告)日：2014-05-22

申请号：CA2889618

申请日：2013-11-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  GLAHN JORN A

IPC: F02C7/20 ,  F01D25/24 ,  F02K3/072

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 a higher pressure turbine is at a ratio between about 0.5 and about 1.5. In addition, the lower pressure turbine is mounted with a first bearing mounted in a mid-turbine frame, and a second bearing mounted within a turbine exhaust case.

公开(公告)号：CA2854082A1

公开(公告)日：2013-11-14

申请号：CA2854082

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/06

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

公开(公告)号：CA2857351A1

公开(公告)日：2013-10-24

申请号：CA2857351

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  F02C3/04

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

公开(公告)号：CA2951916A1

公开(公告)日：2013-08-08

申请号：CA2951916

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOUSTON DAVID P ,  KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  F01D5/06 ,  F02C3/107 ,  F02K3/06

Abstract: A gas turbine engine includes a fan rotatable about an axis, a 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 fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.

公开(公告)号：CA2857360A1

公开(公告)日：2013-08-08

申请号：CA2857360

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/06

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

公开(公告)号：CA2857359A1

公开(公告)日：2013-08-08

申请号：CA2857359

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/02 ,  F01D1/00

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

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

IPC: B64D27/10 ,  B64D27/40

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.

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

IPC: F02C9/18 ,  B64D27/40 ,  F01D25/28 ,  F02C7/36 ,  F02K1/06 ,  F02K1/15

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

IPC: F02C7/36 ,  F01D25/28 ,  F02C9/18 ,  F02K1/06 ,  F02K1/15

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：FR2574856A1

公开(公告)日：1986-06-20

申请号：FR8518500

申请日：1985-12-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  GRIFFIN JAMES G

IPC: F01D5/08 ,  F02C7/18 ,  F02C7/12