公开(公告)号：EP2971648A4

公开(公告)日：2016-11-30

申请号：EP14778154

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  HASEL KARL L

IPC: F02C3/107 ,  F02C3/04

CPC classification number: F02K3/075 ,  F05D2220/3213 ,  F05D2220/3218

公开(公告)号：EP2834473A4

公开(公告)日：2016-03-02

申请号：EP13837107

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D15/12 ,  F01D1/04 ,  F01D1/26 ,  F02C3/107 ,  F02K3/06

CPC classification number: F02K3/06 ,  F01D1/26 ,  F01D15/12 ,  F02C3/107 ,  F05D2260/40311

公开(公告)号：EP2855875A4

公开(公告)日：2016-01-20

申请号：EP13828247

申请日：2013-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/10 ,  F02C7/36 ,  F02K3/06

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

Abstract: A 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部分。 风扇驱动器通过齿轮减速来驱动风扇。 风扇驱动涡轮部分在第一出口处具有第一出口区域，并且被构造成以第一速度旋转。 第二涡轮部分在第二出口处具有第二出口区域，并且被配置为以比第一速度快的第二速度旋转。 第一性能数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率在约0.5至约1.5之间。

公开(公告)号：EP2809938A4

公开(公告)日：2015-11-04

申请号：EP13744335

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: B63H5/10 ,  B64C11/48 ,  B64C27/10 ,  F02C1/00 ,  F02C1/06 ,  F02C3/00 ,  F02C3/10 ,  F02C3/107 ,  F02C6/00 ,  F02C7/06 ,  F02C7/32 ,  F02C7/36 ,  F02K3/00 ,  F02K3/02 ,  F02K3/072

CPC classification number: F02C7/32 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2260/40311 ,  Y02T50/671

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：EP2809932A4

公开(公告)日：2015-11-04

申请号：EP13743283

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: B63H5/10 ,  B64C11/48 ,  B64C27/10 ,  F02C1/00 ,  F02C1/06 ,  F02C3/00 ,  F02C3/10 ,  F02C3/107 ,  F02C6/00 ,  F02C7/06 ,  F02C7/32 ,  F02C7/36 ,  F02K3/00 ,  F02K3/02 ,  F02K3/072

CPC classification number: F02C7/32 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F05D2260/40311 ,  Y02T50/671

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.

公开(公告)号：EP2809575A4

公开(公告)日：2015-09-16

申请号：EP13775188

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL 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 ,  F02K3/072

CPC classification number: F02K3/072

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：EP3063385A4

公开(公告)日：2017-07-12

申请号：EP14880285

申请日：2014-10-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C1/06 ,  F01D5/18 ,  F02C3/107

CPC classification number: F02C3/107 ,  F01D5/187 ,  F05D2300/606 ,  Y02T50/672 ,  Y02T50/676

公开(公告)号：EP2900980A4

公开(公告)日：2016-05-25

申请号：EP13867624

申请日：2013-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  KOHLENBERG GREGORY A

IPC: F02C9/16 ,  F01D21/04 ,  F02C3/04 ,  F02C7/20 ,  F02C7/32 ,  F02K1/04 ,  F02K3/06 ,  F02K3/075

CPC classification number: F02K3/075 ,  F01D21/045 ,  F02C7/32 ,  F02K1/04 ,  F05D2260/30 ,  F05D2260/311 ,  Y10T29/49245

公开(公告)号：EP2831396A4

公开(公告)日：2016-02-24

申请号：EP13812636

申请日：2013-03-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  MOON FRANCIS R

IPC: F02C7/36 ,  F01D17/14 ,  F02C1/02 ,  F02C3/05 ,  F02C3/067 ,  F02C3/10 ,  F02C3/107 ,  F02C3/13 ,  F02C3/14 ,  F02C6/02 ,  F02C9/18 ,  F02K3/06 ,  F02K3/065 ,  F02K3/072 ,  F02K3/075 ,  F02K3/077

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 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.

公开(公告)号：EP2809939A4

公开(公告)日：2015-11-25

申请号：EP13786893

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: B63H5/10 ,  B64C11/48 ,  B64C27/10 ,  F02C1/00 ,  F02C1/06 ,  F02C3/00 ,  F02C3/10 ,  F02C3/107 ,  F02C3/36 ,  F02C6/00 ,  F02K3/00 ,  F02K3/02 ,  F02K3/04 ,  F02K3/06 ,  F02K3/072

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D9/02 ,  F01D9/065 ,  F02C3/04 ,  F02C3/107 ,  F02C3/36 ,  F02C7/06 ,  F02C9/18 ,  F02K1/78 ,  F02K3/04 ,  F02K3/06 ,  F02K3/072 ,  F04D27/009 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  Y02T50/671

Abstract: A gas turbine engine (20) typically includes a fan section (22), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device such as an epicyclical gear assembly (48) may be utilized to drive the fan section (22) such that the fan section (22) may rotate at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). In such engine architectures, a shaft (40) driven by a fan drive turbine section (46) provides an input to the epicyclical gear assembly (48) that drives the fan section (22) at a speed different than the fan drive turbine section (46) such that both the fan drive turbine section (46) and the fan section (22) can rotate at closer to optimal speeds providing increased performance attributes and performance.