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：US20190106992A1

公开(公告)日：2019-04-11

申请号：US16155913

申请日：2018-10-10

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Balamurugan Srinivasan ,  Sridharan Reghupathy Narayanan ,  Karthikeyan Paramanandam ,  Chandiran Jayamurugan ,  Malak Fouad Malak

IPC: F01D5/18 ,  F02C3/04 ,  F02C7/04 ,  F02C7/18 ,  F01D5/14

Abstract: An airfoil for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage.