Engine article with integral liner and nozzle

Patent metadata

Field	Value
Publication number	US-2020182467-A1
Application number	US-201816212879-A
Country	US
Kind code	A1
Filing date	Dec 7, 2018
Priority date	Dec 7, 2018
Publication date	Jun 11, 2020
Grant date	—

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 core engine article, comprising:
a combustor liner defining a combustion chamber therein, the combustor liner including a plurality of injector ports, the plurality of injector ports having a shape that tapers to a corner on an forward side of the injector ports; and a turbine nozzle, the turbine nozzle including a plurality of airfoils; wherein the combustor liner and turbine nozzle are integral with one another.

2 . The core engine article of claim 1 , wherein the plurality of injector ports have a maximum dimension greater than about 0.1 in (0.254 cm).

3 . The core engine article of claim 1 , wherein the injector ports are diamond-shaped.

4 . The core engine article of claim 1 , further comprising a webbing extending outward from the combustor liner along an extent of a periphery of the injector ports.

5 . The core engine article of claim 1 , wherein the injector ports extend into the combustion chamber.

6 . The core engine article of claim 1 , wherein the turbine nozzle includes an inner annulus and an outer annulus, the inner annulus extends into the combustion chamber, and the combustor liner is arranged between the inner annulus and the outer annulus.

7 . The core engine article of claim 6 , wherein a lip extending from the inner annulus contacts the combustor liner.

8 . The core engine article of claim 6 , wherein the airfoils extend from an exterior of the outer annulus.

9 . The core engine article of claim 1 , wherein an aft end of the combustor liner includes one or more scallops.

10 . A core engine article, comprising:
a combustor liner defining a combustion chamber therein, the combustor chamber including a plurality of injector ports; and a turbine nozzle, the turbine nozzle including a plurality of airfoils, wherein the airfoils are each arranged along an airfoil axis, and an angle α between the airfoil axis and a central axis of the core engine article is greater than about 32 degrees; wherein the combustor liner and turbine nozzle are integral with one another.

11 . The core engine article of claim 10 , wherein the angle α is about 45 degrees.

12 . The core engine article of claim 10 , wherein the turbine nozzle includes an inner annulus and an outer annulus, the inner annulus extends into the combustion chamber, and the combustor liner is arranged between the inner annulus and the outer annulus.

13 . The core engine article of claim 12 , wherein a rib extending from the inner annulus contacts the combustor liner.

14 . The core engine article of claim 12 , wherein the airfoils extend from an exterior of the outer annulus.

15 . The core engine article of claim 1 , wherein an aft end of the combustor liner includes one or more scallops, the scallops configured to accelerate air flowing through the core engine article.

16 . 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.

17 . The method of claim 16 , wherein forming the combustor liner includes forming a plurality of injector ports, and the injector ports have a maximum dimension greater than about 0.1 in (0.254 cm).

18 . The method of claim 17 , wherein the plurality of injector ports having a shape that tapers to a corner on a top side with respect to the build direction.

19 . The method of claim 16 , 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.

20 . The method of claim 19 , 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 about 32 degrees.

Assignees

• United Technologies 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

• F23R3/26

  Controlling the air flow · CPC title

• Y02P10/25

  Process efficiency · CPC title

• F05D2250/82

  Micromachines · CPC title

• F05D2250/80

  Size or power range of the machines · CPC title