公开(公告)号：CA2917906A1

公开(公告)日：2015-01-15

申请号：CA2917906

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROACH JAMES T ,  WATSON CHARLES R ,  COOK GRANT O III ,  SCHWARZ FREDERICK M ,  BUGAJ SHARI L ,  SCHLICHTING KEVIN W

IPC: F02C7/00 ,  B05D1/00 ,  B64D29/00 ,  C25D1/00 ,  C25D5/56 ,  F02C7/30 ,  F02K1/06 ,  F02K3/02 ,  F04D29/44

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

公开(公告)号：SG11201405923XA

公开(公告)日：2014-11-27

申请号：SG11201405923X

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/04

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool.

公开(公告)号：CA2849013C

公开(公告)日：2014-11-18

申请号：CA2849013

申请日：2012-12-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  MERRY BRIAN D ,  DYE CHRISTOPHER M ,  JOHNSON STEVEN B ,  SCHWARZ FREDERICK M

IPC: F02C7/042 ,  B64C7/02 ,  B64D27/40 ,  B64D29/00 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine centeriine axis which drives the gear train, the spool includes a low stage count low pressure turbine. In a further non-limiting embodiment of any of the foregoing gas turbine engine embodiments, the low stage count may include three to six (3-6) stages. Additionally or alternatively, the low stage count may include three (3) stages. Additionally or alternatively, the low stage count may include five (5) or six (6) stages.

公开(公告)号：SG11201402895RA

公开(公告)日：2014-10-30

申请号：SG11201402895R

申请日：2012-12-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SMITH PETER G ,  OCHS STUART S ,  SCHWARZ FREDERICK M

IPC: F02K1/06 ,  F02K3/06 ,  F02K3/075

Abstract: A turbofan engine (10) includes a fan variable area nozzle (42) axially movable relative to the fan nacelle (34) to vary a fan nozzle exit area (44) and adjust a pressure ratio of the fan bypass airflow (B) during engine operation.

公开(公告)号：SG11201403118SA

公开(公告)日：2014-09-26

申请号：SG11201403118S

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  ACKERMANN WILLIAM K ,  KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/02

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：SG11201403011RA

公开(公告)日：2014-08-28

申请号：SG11201403011R

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/075

Abstract: A gas turbine engine (20) typically includes a fan section, 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 section such that the fan section 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 one of the turbine sections (28) provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section (28) such that both the turbine section (28) 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 (20).

公开(公告)号：CA2884976A1

公开(公告)日：2014-06-26

申请号：CA2884976

申请日：2013-09-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOMZER DAVID ,  SCHWARZ FREDERICK M

IPC: F01D5/14 ,  F02C7/00

Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.

公开(公告)号：CA2856912A1

公开(公告)日：2013-10-24

申请号：CA2856912

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/075

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：CA2856561A1

公开(公告)日：2013-10-17

申请号：CA2856561

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GARIEL 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

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：CA2857357A1

公开(公告)日：2013-08-08

申请号：CA2857357

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOUSTON DAVID P ,  KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/02 ,  B63H5/10 ,  F01D1/24

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.