公开(公告)号：US20190136702A1

公开(公告)日：2019-05-09

申请号：US15808214

申请日：2017-11-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Vinayender Kuchana ,  Balamurugan Srinivasan ,  Craig Mckeever ,  Malak Fouad Malak

IPC: F01D9/04

Abstract: A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.

公开(公告)号：US20190003325A1

公开(公告)日：2019-01-03

申请号：US15416144

申请日：2017-01-26

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Vinayender Kuchana ,  Paul Couey ,  Balamurugan Srinivasan ,  Craig Mckeever ,  Malak Fouad Malak

IPC: F01D9/06 ,  F01D5/14 ,  F01D9/02 ,  F02C3/13

Abstract: A turbine section of a gas turbine engine is provided. The turbine section includes a first turbine with a first inlet and a first outlet; second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least two splitter blades disposed within the inter-turbine duct. The at least two splitter blades include a first splitter blade and a second splitter blade radially interior to the first splitter blade. At least the second splitter blade has a radial position that is greater than 60% of a distance from the shroud to the hub.

公开(公告)号：US20200240278A1

公开(公告)日：2020-07-30

申请号：US16677020

申请日：2019-11-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Vinayender Kuchana ,  Balamurugan Srinivasan ,  Craig Mckeever ,  Malak Fouad Malak

IPC: F01D9/04 ,  F01D5/14

Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.

公开(公告)号：US11131205B2

公开(公告)日：2021-09-28

申请号：US16677020

申请日：2019-11-07

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Vinayender Kuchana ,  Balamurugan Srinivasan ,  Craig Mckeever ,  Malak Fouad Malak

IPC: F01D9/04 ,  F01D9/02

Abstract: A turbine section for a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first outlet, and a second turbine with a second inlet. The turbine section includes an inter-turbine duct extending from the first outlet to the second inlet and configured to direct a flow along a flow direction. The inter-turbine duct is defined by a hub and a shroud. The turbine section includes at least a first splitter blade positioned between the hub and the shroud. The first splitter blade includes a pressure side, a suction side, and at least one vortex generating structure having a leading end opposite a trailing end positioned on the suction side such that a first angle is defined between the vortex generating structure and the flow direction. The vortex generating structure extends in a radial direction from the suction side toward the hub.