Honeywell International Inc.

James Neumann

Harry Lester Kington

Mark C Morris

Rodolphe Dudebout

David R Waldman

William J Howe

Art Payne

Dustin Brandt

An inter-turbine duct includes a first annular wall with a ceramic composite material and including a first plurality of layers and a second plurality of layers, the first plurality of layers including a slot extending therethrough; and a first vane with a material of a metal alloy or a ceramic material. The first vane has a first end and a flange extending through the slot with the flange extending away from the first end and being retained between the first plurality of layers and the second plurality of layers of the first annular wall.

Inter-turbine ducts

Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner. The impingement chamber connects to an entry hole on the cold side annular surface and includes a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to an exit hole positioned on the hot side annular surface of the annular liner portion. The first metering hole is connected to the impingement chamber. The cooling air outlet passageway directs the air onto the hot side annular surface and spreads the airflow axially and laterally parallel to the hot side annular surface. Furthermore, a ratio of a radial thickness of the annular liner portion to a diameter of the entry hole is from about 2 to about 6.

Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniques

In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations.

Turbine stator airfoils with individual orientations

Method of making turbine stator airfoils with individual orientations

Compressor impellers, compressor sections, and methods of manufacturing compressor impellers and cooling the compressor impellers are provided. In an embodiment, and by way of example only, a compressor impeller includes a bore section and a rim section. The bore section comprises a first nickel-based alloy and includes an inner disk portion and a first plurality of blade portions extending therefrom. The rim section comprises a second nickel-based alloy and includes an outer disk portion and a second plurality of blade portions. The outer disk portion is bonded to the inner disk portion of the bore section, and the second plurality of blade portions is bonded to the first plurality of blade portions of the bore section.

Growing community of inventors

Tempe, AZ, United States of America

James Neumann