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    КОМПОНОВКА РЕДУКТОРНОГО ТУРБОВЕНТИЛЯТОРНОГО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ
    52.
    发明专利
    КОМПОНОВКА РЕДУКТОРНОГО ТУРБОВЕНТИЛЯТОРНОГО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ 未知

    公开(公告)号：RU2633218C2

    公开(公告)日：2017-10-11

    申请号：RU2014134426

    申请日：2013-01-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  SHVARTS FREDERIK M

    IPC: F02K3/06

    Abstract: Газотурбинныйдвигательсодержитвентиляторнуюсекцию, компрессорнуюсекцию, секциюкамерысгоранияи турбиннуюсекцию. Дляприведенияв движениевентиляторнойсекцииможетбытьиспользованредуктор, например, представляющийсобойэпициклическуюзубчатуюпередачу, так, чтобыобеспечитьвозможностьвращениявентиляторнойсекциисоскоростью, отличнойотскоростивращениятурбиннойсекции. Турбиннаясекциясообщаетсяпотекучейсредес камеройсгоранияи содержиттурбинуприводавентилятораи вторуютурбину, причемтурбинаприводавентиляторасодержитмножествоступенейтурбины. Вентиляторимеетмножестволопаток, вращаемыхвокругоси, причемотношениечислалопатоквентиляторак числуступенейтурбинысоставляетот 2,5 до 8,5. Турбинаприводавентиляторасодержитпервыйзаднийротор, прикрепленныйк первомувалу, автораятурбинасодержитвторойзаднийротор, прикрепленныйковторомувалу. Аксиальнопозадипервогосоединениямеждупервымзаднимротороми первымваломрасположенпервыйподшипниковыйузел, ааксиальнопередвторымсоединениеммеждувторымзаднимротороми вторымваломрасположенвторойподшипниковыйузел. Втораятурбинаимеетпоменьшеймередвеступении способнаработатьприпервомдавлении, атурбинаприводавентилятораимеетболеедвухступенейи способнаработатьпривторомдавлении, котороеменьше, чемпервоедавление. Обеспечиваетсяповышениерабочиххарактеристики производительностизасчетиспользованиятребуемыхсочетанийраскрытыхконструктивныхособенностейразличныхкомпонентовописанногогазотурбинногодвигателя. 18 з.п. ф-лы, 12 ил.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    54.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    公开(公告)号：CA2951916C

    公开(公告)日：2017-05-09

    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.

    GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION
    55.
    发明专利
    GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION 未知

    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.

    motor de turbina a gás
    56.
    发明专利
    motor de turbina a gás 未知

    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.

    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
    57.
    发明专利
    GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 未知

    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.

    REVERSE CORE GEAR TURBOFAN
    60.
    发明专利
    REVERSE CORE GEAR TURBOFAN 未知

    公开(公告)号：SG11201404963VA

    公开(公告)日：2014-10-30

    申请号：SG11201404963V

    申请日：2013-03-26

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL BERNARD ,  MOON FRANCIS R

    Abstract: A method of operating a gas turbine engine comprising the steps of: (a) operating a turbine section having blades with a radially outermost extent, and a flow diverter that is operable to divert air radially inwardly of the radially outermost extent of the turbine blades, or allow air to pass radially outwardly of the radially outermost extent of the turbine blades; and (b) positioning said flow diverter to increase or decrease the amount of gas passing across that turbine section to increase or decrease a power output by said turbine section.

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