GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION

    公开(公告)号:CA2945265A1

    公开(公告)日:2017-05-09

    申请号:CA2945265

    申请日:2016-10-12

    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.

    motor de turbina a gás
    52.
    发明专利

    公开(公告)号:BR102016005926A2

    公开(公告)日:2016-10-25

    申请号:BR102016005926

    申请日:2016-03-17

    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.

    GEARED TURBOFAN ENGINE WITH HIGH COMPRESSOR EXIT TEMPERATURE

    公开(公告)号:CA2923326A1

    公开(公告)日:2016-09-20

    申请号:CA2923326

    申请日:2016-03-08

    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.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

    公开(公告)号:CA2923329A1

    公开(公告)日:2016-09-19

    申请号:CA2923329

    申请日:2016-03-08

    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.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

    公开(公告)号:SG11201403015WA

    公开(公告)日:2014-09-26

    申请号:SG11201403015W

    申请日:2013-01-30

    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.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

    公开(公告)号:SG11201402823TA

    公开(公告)日:2014-09-26

    申请号:SG11201402823T

    申请日:2013-01-30

    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.

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