NOZZLE AND VANE SYSTEM FOR NACELLE ANTI-ICING

Title:

NOZZLE AND VANE SYSTEM FOR NACELLE ANTI-ICING

Document Type and Number:

Japanese Patent JP2017141015

Kind Code:

A

Abstract:

PROBLEM TO BE SOLVED: To provide an anti-icing system that reduces a direct impingement of a high temperature gas stream on an inner surface of an inlet lip of a jet turbine engine for an aircraft.SOLUTION: A system 1 includes vanes 56 extending from a bulkhead into an annular housing volume 44. Each vane includes a first end 66 coupled to the bulkhead, a free end 68 extending into the annular housing volume, and a vane body 67 extending therebetween. The vanes are positioned downstream from a nozzle 34 and configured to direct a high temperature gas stream 50 into the annular housing volume in a first direction 58. The vanes 56 are configured to redirect the high temperature gas stream through a first turn angle from the first direction to a second direction 60. The second direction reduces a direct impingement 52 of the high temperature gas stream 50 on an inner surface 62 of the inlet lip 14.SELECTED DRAWING: Figure 5

Inventors:

CLARK GEORGE WIBERG
SHILADITYA MUKHERJEE

Application Number:

JP2017006382A

Publication Date:

August 17, 2017

Filing Date:

January 18, 2017

Export Citation:

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