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.

公开(公告)号：SG11201403015WA

公开(公告)日：2014-09-26

申请号：SG11201403015W

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.

公开(公告)号：CA2951916A1

公开(公告)日：2013-08-08

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.

公开(公告)号：DE69736570D1

公开(公告)日：2006-10-05

申请号：DE69736570

申请日：1997-06-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GONSOR MICHAEL ,  KELLEY III SANFORD E ,  HOUSTON DAVID P

IPC: F01D5/10 ,  F01D5/22 ,  F01D5/26 ,  F01D5/30 ,  F01D11/00 ,  F16F7/00 ,  F16F15/02

Abstract: A damper and seal assembly for a turbine rotor includes a damper (40) and a seal (42), the seal having a projection (70) that interferes with a blade (10) of the turbine if the damper and seal are incorrectly installed. The invention also extends to the seal per se.

公开(公告)号：DE69727727D1

公开(公告)日：2004-04-01

申请号：DE69727727

申请日：1997-06-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GONSOR MICHAEL ,  KELLY III SANFORD E ,  HOUSTON DAVID P

IPC: F01D5/10 ,  F01D5/22 ,  F01D5/26 ,  F01D5/30 ,  F01D11/00 ,  F16F7/00 ,  F16F15/02

Abstract: A damper and seal assembly for a turbine rotor includes a damper (40) and a seal (42), the seal having a projection (70) that interferes with a blade (10) of the turbine if the damper and seal are incorrectly installed. The invention also extends to the seal per se.

公开(公告)号：CA2857357C

公开(公告)日：2017-06-06

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: F02C7/36 ,  F01D1/24 ,  F01D5/06 ,  F02C3/04 ,  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.

公开(公告)号：CA2923331A1

公开(公告)日：2016-09-19

申请号：CA2923331

申请日：2016-03-08

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02C7/36

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.

公开(公告)号：SG11201406226VA

公开(公告)日：2015-01-29

申请号：SG11201406226V

申请日：2013-04-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  HOUSTON DAVID P ,  TRACY ANITA L

IPC: F01D5/12 ,  F01C7/00 ,  F01D5/18 ,  F01K3/00

Abstract: An airfoil (60) includes an airfoil body (68) that has a leading edge (LE) and a trailing edge (TE) and a first sidewall (74) and a second sidewall (76) that is spaced apart from the first sidewall (74). The first sidewall (74) and the second sidewall (76) join the leading edge (LE) and the trailing edge (TE) and at least partially define a cavity (78) in the airfoil body (68). A damper member (88) is enclosed in the cavity (78) and is loose within the cavity (78).

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.

公开(公告)号：DE69728508D1

公开(公告)日：2004-05-13

申请号：DE69728508

申请日：1997-12-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOUSTON DAVID P ,  AIREY DAVID ,  PELLAND NATALIE A

IPC: F01D5/30 ,  F01D11/00 ,  F01D5/22

Abstract: A seal for a turbine blade in a gas turbine engine has a sealing portion 72 with two subportions 80,82, where the subportions 80,82 are longitudinally offset from one another, so that the seal may provide sealing for adjacent turbine blades having longitudinally offset inner platform surfaces.