公开(公告)号：WO2014007880A3

公开(公告)日：2014-03-20

申请号：PCT/US2013033776

申请日：2013-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  MOON FRANCIS R

IPC: F02C7/36 ,  F02C3/067 ,  F02K3/072

CPC classification number: F02C6/02 ,  F01D17/141 ,  F02C3/05 ,  F02C3/10 ,  F02C3/107 ,  F02C3/13 ,  F02C3/145 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06 ,  F02K3/065 ,  F02K3/075 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2250/36 ,  F05D2260/4023 ,  F05D2260/4031 ,  F05D2270/053

Abstract: A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.

Abstract translation: 燃气涡轮发动机在轴向外部位置具有风扇。 风扇绕旋转轴旋转。 风扇将空气输送到外部旁路管道中，并且跨过位于外部旁路管道的径向内侧的增压风扇。 增压风扇将空气输送到径向中间的管道中，并且将冷却涡轮机转入径向内部的芯管道，将其导入压缩机。 从压缩机，空气沿着朝向风扇的方向通过燃烧器部分轴向流动，并且沿着涡轮机部分的排气指向中间管道。 齿轮减速器从风扇驱动涡轮机部分驱动风扇。 还公开了一种方法。

公开(公告)号：WO2014025441A2

公开(公告)日：2014-02-13

申请号：PCT/US2013041797

申请日：2013-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/06

CPC classification number: F02C3/113 ,  F02C7/36 ,  F02K3/02 ,  F02K3/06 ,  F02K3/075

Abstract: gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. A second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed that is faster than the first 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. A ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5.

Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子以及三个涡轮区段。 风扇驱动通过齿轮减速来驱动风扇。 风扇驱动涡轮部分在第一出口点处具有第一出口区域并且构造成以第一速度旋转。 第二涡轮机部分在第二出口点处具有第二出口区域并且构造成以比第一速度更快的第二速度旋转。 第一表现量被定义为第一速度平方和第一区域的乘积。 第二性能量被定义为第二速度平方和第二区域的乘积。 第一性能量与第二性能量的比例在大约0.5和大约1.5之间。

公开(公告)号：WO2013165515A3

公开(公告)日：2014-01-23

申请号：PCT/US2013025802

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D5/06 ,  F01D5/02 ,  F02C7/04

CPC classification number: F01D15/12 ,  F02C7/047 ,  F02C7/36 ,  F02K3/072 ,  F05D2260/40311

Abstract: A gas turbine engine includes a shaft, a speed change device driven by the shaft, and a fan including a fan rotor driven by the speed change device. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract translation: 燃气涡轮发动机包括轴，由轴驱动的变速装置和包括由变速装置驱动的风扇转子的风扇。 至少一个诱导器台被定位在风扇的后面，并被联接成与风扇转子一起旋转。

公开(公告)号：WO2013165521A3

公开(公告)日：2013-12-27

申请号：PCT/US2013026075

申请日：2013-02-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D5/04 ,  F01D5/02 ,  F02C7/04

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311

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.

Abstract translation: 燃气涡轮发动机包括限定旋转轴线的第一轴和能够围绕旋转轴线旋转并相对于第一轴径向向外间隔开的第二轴。 变速机构由第二轴驱动。 风扇包括由变速机构驱动的风扇转子，使得风扇和第一轴以比第二轴更慢的速度旋转。 至少一个诱导器台被定位在风扇的后面，并被联接成与风扇转子一起旋转。

公开(公告)号：CA2933432C

公开(公告)日：2018-05-01

申请号：CA2933432

申请日：2016-06-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C7/36

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：RU2639821C2

公开(公告)日：2017-12-22

申请号：RU2014110925

申请日：2014-03-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MAKKUN MAJKL E ,  KHAZBEND DZHEJSON ,  SHVARTS FREDERIK M ,  KUPRATIS DANIEL BERNARD ,  SUSYU GABRIEL L ,  AKERMANN UILYAM K

IPC: F02C7/20 ,  F02C7/36 ,  F02K3/068

Abstract: Газотурбинныйдвигательсодержитгибкуюопорудлязубчатойпередачиприводавентилятора. Перваятурбиннаясекцияимеетпервуювыходнуюплощадьи способнавращатьсяс первойскоростью. Втораятурбиннаясекцияимеетвторуювыходнуюплощадьи способнавращатьсясовторойскоростью, превышающейпервуюскорость. Первыйхарактеризующийпараметрявляетсяпроизведениемквадратапервойскоростии первойплощадивыхода, второйхарактеризующийпараметрявляетсяпроизведениемквадратавторойскоростии второйплощадивыхода. Отношениепервогохарактеризующегопараметраковторомухарактеризующемупараметрунаходитсяв интервалеот 0,5 до 1,5. Рамаимеетбоковуюжесткостьрамыи поперечнуюжесткостьрамы, агибкаяопораимеетпоперечнуюжесткостьгибкойопорыи боковуюжесткостьгибкойопоры. Боковаяжесткостьгибкойопорыменьшеуказаннойбоковойжесткостирамы, ауказаннаяпоперечнаяжесткостьгибкойопорыменьшеуказаннойпоперечнойжесткостирамы. Отношениесилытяги, обеспечиваемойуказаннымдвигателем, кобъемутурбиннойсекции, включающейв себякакуказаннуютурбинувысокогодавления, таки указаннуютурбинунизкогодавления, большеилиравно 1,5 именьшеилиравно 5,5 фунт-сила/дюйм, причемуказаннаятягаявляетсярасчетнойстатическойтягойпривзлетес уровняморя. Достигаетсяуменьшениетурбиннойсекциикакв отношениидиаметра, таки вотношенииосевойдлины, атакжеувеличениеКПДи срокаслужбыгазотурбинногодвигателя. 3 н. и 15 з.п. ф-лы, 11 ил., 1 табл.

公开(公告)号：CA2857360C

公开(公告)日：2017-12-12

申请号：CA2857360

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C7/36 ,  F01D25/16 ,  F02C7/06 ,  F02K3/06

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：BR102016000310A2

公开(公告)日：2016-10-04

申请号：BR102016000310

申请日：2016-01-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C7/00 ,  H02K7/18

Abstract: turbina de motor de turbina a gás uma turbina do motor de turbina a gás tem uma turbina de alta pressão configurada para rodar com um compressor de alta pressão como um carretel de alta pressão numa primeira direção em volta de um eixo central e uma turbina de baixa pressão configurada para rodar com um compressor de baixa pressão, como um carretel de baixa pressão na primeira direção em torno do eixo central. uma densidade de potência é maior do que ou igual a cerca de 1,5 e inferior ou igual a cerca de 5.5 lbf/polegadas cúbicas. um ventilador está ligado ao carretel de baixa pressão por meio de um mecanismo de mudança de velocidade e roda numa segunda direção oposta à primeira direção.

公开(公告)号：CA2915343A1

公开(公告)日：2016-07-09

申请号：CA2915343

申请日：2015-12-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/06 ,  F01D9/02 ,  F02C7/36

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

公开(公告)号：SG11201404986TA

公开(公告)日：2014-11-27

申请号：SG11201404986T

申请日：2013-02-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F04B17/00