公开(公告)号：US20170218975A1

公开(公告)日：2017-08-03

申请号：US15009868

申请日：2016-01-29

Applicant: United Technologies Corporation

Inventor： Matthew E. Bintz ,  Frederick M. Schwarz ,  Yuan Dong

IPC: F04D29/36 ,  F04D29/52 ,  F04D25/02 ,  F04D29/56 ,  F02K3/06 ,  F01D5/02 ,  F04D25/04 ,  F04D19/00 ,  F02K1/72

CPC classification number: F02K1/72 ,  F01D7/00 ,  F02K1/09 ,  F04D25/028 ,  F04D29/323 ,  F05D2260/40311 ,  F05D2260/70 ,  F05D2260/74 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades rotatable about an engine axis. Each of the fan blades have a leading edge and rotate about a fan blade axis. A method of operating a gas turbine engine is also disclosed.

公开(公告)号：US20170218850A1

公开(公告)日：2017-08-03

申请号：US15485563

申请日：2017-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/36 ,  F04D25/04 ,  F01D5/06 ,  F04D29/32

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.

公开(公告)号：US20170218789A1

公开(公告)日：2017-08-03

申请号：US15485512

申请日：2017-04-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F02K3/06 ,  F04D29/053 ,  F01D5/06 ,  F04D19/00 ,  F04D25/04

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.

公开(公告)号：US20170175767A1

公开(公告)日：2017-06-22

申请号：US14974138

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  David A. Welch

IPC: F04D29/52 ,  F04D29/66 ,  F02K3/06 ,  F02C3/04 ,  F02C7/36 ,  F04D19/00 ,  F04D25/02

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. At least a portion of the nacelle inner surface extends radially inwardly to be radially inward of an outer diameter of the fan blades. The inner surface of the nacelle is formed with a trench, which extends into the inner surface to a radially outer extent that is spaced radially outward of the outer diameter of the fan blades.

公开(公告)号：US20170175629A1

公开(公告)日：2017-06-22

申请号：US14974169

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Joseph Murphy

IPC: F02C7/047 ,  F04D29/32 ,  F04D29/38 ,  F02C7/36 ,  F02C3/04 ,  F02K3/06 ,  F04D19/00 ,  F04D29/52

CPC classification number: F02C7/047 ,  F02C3/04 ,  F02C7/045 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D29/325 ,  F04D29/38 ,  F04D29/522 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/4031

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle, and the outer nacelle having an inner surface. A distance is defined between an axial outer end of the nacelle, and a leading edge of the fan blade. An anti-icing treatment is provided to an inner periphery of the nacelle over at least 75% of the distance along the inner periphery of the nacelle.

公开(公告)号：US20170152756A1

公开(公告)日：2017-06-01

申请号：US14935673

申请日：2015-12-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan ,  Michael E. McCune ,  Gabriel L. Suciu

IPC: F01D15/12 ,  F16H1/28 ,  F16H57/04 ,  F02K3/06 ,  F01D25/18

CPC classification number: F01D15/12 ,  F01D25/18 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/50 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H57/0479 ,  F16H57/0486

Abstract: A gas turbine engine has a fan rotor, a turbine rotor driving the fan rotor, and an epicyclic gear reduction positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine is configured to drive the sun gear to, in turn, drive the ring gears to, in turn, drive the fan rotor.

公开(公告)号：US20170122215A1

公开(公告)日：2017-05-04

申请号：US15393697

申请日：2016-12-29

Applicant: United Technologies Corporation

Inventor： David P. Houston ,  Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C7/36 ,  F01D5/06 ,  F04D29/32 ,  F02K3/06 ,  F02K1/78 ,  F02C3/04 ,  F01D9/04

CPC classification number: F02K3/06 ,  F01D5/02 ,  F01D5/06 ,  F01D9/02 ,  F01D9/041 ,  F01D25/164 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02C9/18 ,  F02K1/78 ,  F02K3/072 ,  F04D27/009 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/40 ,  F05D2250/30 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671 ,  Y02T50/673

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：US20170122210A1

公开(公告)日：2017-05-04

申请号：US15412729

申请日：2017-01-23

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  John T. Schmitz

IPC: F02C7/18

CPC classification number: F02C7/185 ,  B64D33/08 ,  B64D33/10 ,  B64D33/12 ,  B64D2033/024 ,  F01D25/08 ,  F01D25/14 ,  F02C7/12 ,  F02C7/14 ,  F02C7/32 ,  F02K3/077 ,  F02K3/105 ,  F02K3/115 ,  F05D2260/20 ,  F05D2260/213 ,  F28D2021/0021 ,  F28D2021/0026 ,  Y02T50/675

Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

公开(公告)号：US20170114724A1

公开(公告)日：2017-04-27

申请号：US15399864

申请日：2017-01-06

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/36 ,  F02C7/06 ,  F01D5/06 ,  F04D29/32 ,  F02C3/06 ,  F02K3/06

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D25/162 ,  F02C3/06 ,  F02C3/107 ,  F02C7/06 ,  F02K3/06 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

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 supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

公开(公告)号：US09631558B2

公开(公告)日：2017-04-25

申请号：US13908177

申请日：2013-06-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D15/12

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.