Engine article with integral liner and nozzle

Patent metadata

Field	Value
Publication number	US-11612938-B2
Application number	US-202217591054-A
Country	US
Kind code	B2
Filing date	Feb 2, 2022
Priority date	Dec 7, 2018
Publication date	Mar 28, 2023
Grant date	Mar 28, 2023

Abstract

A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

First claim

What is claimed is:

1. A method of making a core engine article, comprising:
depositing material using an additive manufacturing technique to form a turbine nozzle in a build direction, and
depositing material using the additive manufacturing technique to form a combustor liner in the build direction, wherein the combustor liner is supported by the turbine nozzle during the build.

2. The method of claim 1 ,
wherein forming the combustor liner includes forming a plurality of injector ports, and the injector ports have a maximum dimension greater than 0.1 in (0.254 cm).

3. The method of claim 2 , wherein the plurality of injector ports have a shape that tapers to a corner on a top side with respect to the build direction.

4. The method of claim 3 , wherein the plurality of injector ports are diamond-shaped.

5. The method of claim 2 ,
wherein forming the plurality of injector ports includes forming a webbing extending outward from the combustor liner along an extent of a periphery of the plurality of the injector ports.

6. The method of claim 5 , wherein forming the turbine nozzle includes forming a plurality of airfoils on an outer surface of the turbine nozzle, the airfoils having an orientation with respect to the build direction such that they are self-supporting during the build.

7. The method of claim 6 ,
wherein the airfoils are each built along an airfoil axis, and
an angle α between the airfoil axis and the build direction is greater than 32 degrees.

8. The method of claim 7 ,
wherein the angle α is 45 degrees.

Assignees

• Raytheon Tech Corp

Inventors

• Binek Lawrence
• Boyer Jesse R
• Voytovych Dmytro Mykolayovych

Classifications

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F02C3/045

  having compressor and turbine passages in a single rotor-module (F02C3/073 takes precedence) · CPC title

• F23R3/16

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title