公开(公告)号：BR102016000128A2

公开(公告)日：2016-10-04

申请号：BR102016000128

申请日：2016-01-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C6/02 ,  F02C3/04 ,  F02C7/36 ,  F02K3/04 ,  F02K3/06

Abstract: turbina de motor de turbina a gás, e, motor uma turbina de motor de turbina a gás tem uma turbina de alta pressão configurada para girar com um compressor de alta pressão como um carretel de alta pressão numa primeira direção em torno de um eixo central e uma turbina de baixa pressão configurada para girar com um compressor de baixa pressão como um carretel de baixa pressão na primeira direção em torno do eixo central. uma densidade de energia é maior ou igual a cerca de 1,5 e menor ou igual a cerca de 5,5 lbf/polegadas cúbicas. um ventilador é conectado ao carretel de baixa pressão via um mecanismo de mudança de velocidade e gira na primeira direção.

公开(公告)号：CA2923331A1

公开(公告)日：2016-09-19

申请号：CA2923331

申请日：2016-03-08

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C7/36

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：CA2857351C

公开(公告)日：2016-06-28

申请号：CA2857351

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  F01D25/16 ,  F02C3/113 ,  F02C7/06

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：SG11201405923XA

公开(公告)日：2014-11-27

申请号：SG11201405923X

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/04

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool.

公开(公告)号：SG11201403118SA

公开(公告)日：2014-09-26

申请号：SG11201403118S

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：SG11201403011RA

公开(公告)日：2014-08-28

申请号：SG11201403011R

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/075

Abstract: A gas turbine engine (20) typically includes a fan section, a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device (48) 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 (28) so as to increase the overall propulsive efficiency of the engine (20). In such engine architectures, a shaft (40) driven by one of the turbine sections (28) provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section (28) such that both the turbine section (28) 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 (20).

公开(公告)号：CA2856912A1

公开(公告)日：2013-10-24

申请号：CA2856912

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/075

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：CA2856561A1

公开(公告)日：2013-10-17

申请号：CA2856561

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: B63H5/10 ,  B64C11/48 ,  B64C27/10 ,  F02C1/00 ,  F02C1/06 ,  F02C3/00 ,  F02C3/10 ,  F02C6/00 ,  F02K3/00 ,  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：CA2857357A1

公开(公告)日：2013-08-08

申请号：CA2857357

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02K3/02 ,  B63H5/10 ,  F01D1/24

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：CA2853839A1

公开(公告)日：2013-08-08

申请号：CA2853839

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C3/113 ,  F02C3/06

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. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing.