公开(公告)号：CA2945265A1

公开(公告)日：2017-05-09

申请号：CA2945265

申请日：2016-10-12

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C7/36 ,  F02C7/06

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan having one or more fan blades. A compressor section is in fluid communication with the fan. The compressor section includes a first compressor section and a second compressor section. A turbine section is in fluid communication with the compressor section. The turbine section includes a first turbine section and a second turbine section. The first turbine section has a first exit area at a first exit point and rotates at a first speed. The second turbine section has a second exit area at a second exit point and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：BR102016005926A2

公开(公告)日：2016-10-25

申请号：BR102016005926

申请日：2016-03-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C3/107 ,  F02K3/04 ,  F16H1/00

Abstract: um motor de turbina a gás, normalmente, possui uma seção de ventoinha, uma seção de compressor, uma seção de combustor e uma seção de turbina. um dispositivo de redução de velocidade, tal como um conjunto de transmissão epicíclico pode ser utilizado para acionar a seção do ventoinha, de tal modo que a seção do ventoinha possa girar a uma velocidade diferente da seção de turbina, de modo a aumentar a eficiência global de propulsão do motor. em tais arquiteturas de motor, um eixo acionado por uma das seções de turbina fornece uma entrada para o conjunto de engrenagens epicicloidais, o que impulsiona a seção de ventoinha a uma velocidade diferente do que a da seção de turbina, de modo a que tanto a seção de turbina e a seção de ventoinha podem girar em velocidades mais próximas da velocidade ótima, que proporciona maiores atributos de desempenho e desempenho por combinações desejáveis das características divulgadas dos vários componentes do motor de turbina a gás descrito e divulgado.

公开(公告)号：CA2923326A1

公开(公告)日：2016-09-20

申请号：CA2923326

申请日：2016-03-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  HASEL KARL L

IPC: F02C7/36

Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000 °F and about 1500 °F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

公开(公告)号：CA2923329A1

公开(公告)日：2016-09-19

申请号：CA2923329

申请日：2016-03-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  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：BR102014007285A2

公开(公告)日：2015-05-26

申请号：BR102014007285

申请日：2014-03-26

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C7/20

Abstract: Motor de turbina a gás um motor de turbina a gás inclui um suporte flexivel para um sistema de engrenagens de acionamento de ventoinha. Uma turbina de acionamento de ventoinha a alta velocidade aciona o sistema de engrenagens de acionamento da ventoinha.

公开(公告)号：SG11201405922SA

公开(公告)日：2014-10-30

申请号：SG11201405922S

申请日：2013-04-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCUNE MICHAEL E ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  F01D21/00

公开(公告)号：SG11201405143XA

公开(公告)日：2014-10-30

申请号：SG11201405143X

申请日：2013-02-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D5/04 ,  F01D5/02 ,  F02C7/04

Abstract: A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

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：SG11201403015WA

公开(公告)日：2014-09-26

申请号：SG11201403015W

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：SG11201402823TA

公开(公告)日：2014-09-26

申请号：SG11201402823T

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 (20) includes a fan (42), 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 (42) at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). A shaft driven (30) by the turbine section (28) provides an input to the epicyclical gear assembly (48) such that both the turbine section (28) and the fan (42) can rotate at closer to optimal speeds providing increased performance attributes and performance.