公开(公告)号：SG11201403614VA

公开(公告)日：2014-10-30

申请号：SG11201403614V

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C3/06 ,  F02C3/113

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.

公开(公告)号：CA2856561C

公开(公告)日：2017-05-30

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: F02K3/072 ,  F02C3/107 ,  F02C7/36

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：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：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：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.

公开(公告)号：CA2856723C

公开(公告)日：2021-09-07

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: F02C3/107 ,  F02K3/02 ,  F02K3/06

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.

公开(公告)号：BR102014020190A2

公开(公告)日：2015-09-22

申请号：BR102014020190

申请日：2014-08-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M ,  SUCIU GABRIEL L ,  HUSBAND JASON ,  MCCUNE MICHAEL E ,  SHERIDAN WILLIAM G ,  ACKERMANN WILLIAM K

IPC: F02C3/113

Abstract: motor de turbina a gás. um sistema de engrenagem de acionamento da ventoinha para um motor de turbina a gás inclui um sistema de engrenagem que proporciona uma reducão de velocidade entre uma turbina de acionamento da ventoinha e uma ventoinha e uni apoio flexivelmente suportando porções do sistema de engrenagem. uni sistenía de lubrificação suportando o sistema de engrenageni de acionamento da ventoinha fornece o lubrificante para o sistema de engrenagem e remove energia térmica produzida pelo sistema de engrenagem.o sistema de lubrificação inclui uma capacidade para a remoção de energia igual a menos do cerca de 2¨% de entrada de energia para o sistema de engrenagem.

公开(公告)号：IN2690DE2014A

公开(公告)日：2015-06-26

申请号：IN2690DE2014

申请日：2014-09-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SHERIDAN WILLIAM G ,  MCCUNE MICHAEL E ,  SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  SUCIU GABRIEL L ,  ACKERMANN WILLIAM K ,  HUSBAND JASON

IPC: F02C7/06

Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.

公开(公告)号：CA2845618C

公开(公告)日：2015-06-02

申请号：CA2845618

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  HUSBAND JASON ,  SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  SUCIU GABRIEL L ,  ACKERMANN WILLIAM K

IPC: F02C7/36 ,  F01D25/24 ,  F02C7/00 ,  F16H1/48 ,  F16H57/021

Abstract: A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

公开(公告)号：CA2845618A1

公开(公告)日：2014-05-22

申请号：CA2845618

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  HUSBAND JASON ,  SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  SUCIU GABRIEL L ,  ACKERMANN WILLIAM K

IPC: F02C7/36 ,  F01D25/24 ,  F02C7/00 ,  F16H1/48 ,  F16H57/021

Abstract: A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.