Combustion systems

Patent metadata

Field	Value
Publication number	US-2016376997-A1
Application number	US-201514752318-A
Country	US
Kind code	A1
Filing date	Jun 26, 2015
Priority date	Jun 26, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

A combustion system for a gas turbine engine includes a combustor dome. The combustor dome includes a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome. The fuel manifold and nozzle components are integrated with the combustor dome for fluid communication from the inlet to the nozzle components.

First claim

What is claimed is:

1 . A combustion system for a gas turbine engine comprising:
a combustor dome including a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome wherein the fuel manifold and nozzle components are integrated with the combustor dome for fluid communication from the inlet to the nozzle components.

2 . A combustion system as recited in claim 1 , wherein the inlet is radially outboard of the nozzle components for supplying fuel to the manifold from a source external to the combustor dome.

3 . A combustion system as recited in claim 1 , wherein the nozzle components include a wetted inner nozzle wall in fluid communication with the fuel manifold for each nozzle.

4 . A combustion system as recited in claim 3 , wherein the nozzle components include a respective fuel distributor outboard of the wetted inner nozzle wall for each nozzle, wherein a fuel circuit is defined between the wetted inner nozzle wall and the fuel distributor of each nozzle.

5 . A combustion system as recited in claim 1 , wherein the nozzle components of each nozzle include a fuel circuit outboard of an inner air passage.

6 . A combustion system as recited in claim 5 , wherein the nozzle components of each nozzle include an inner insulation shell lining the inner air passage, and an outer insulation shell lining the nozzle outboard of the fuel circuit.

7 . A combustion system as recited in claim 5 , wherein the nozzle components of each nozzle include a radial swirler upstream of the inner air passage for swirling air flowing into the inner air passage.

8 . A combustion system as recited in claim 7 , wherein each radial swirler is mounted to the combustor dome with fasteners passing through radial swirler vanes of the radial swirler, wherein the radial swirler vanes are hollow to permit radial thermal expansion of the radial swirler independent from the combustor dome.

9 . A combustion system as recited in claim 1 , wherein the fuel manifold forms an outer combustor dome ring, wherein the nozzle components extend from the outer combustor dome ring radially inward to an inner combustor dome ring.

10 . A combustion system as recited in claim 9 , wherein the inner combustor dome ring is circumferentially segmented to accommodate thermal expansion and contraction of the combustor dome.

11 . A combustion system as recited in claim 9 , further comprising an outer cowl extending from the outer combustor dome ring and an inner cowl extending from the inner combustor dome ring, wherein the inner and outer cowlings cooperate to form an annular diverging inlet for feeding compressor discharge air to the nozzles.

12 . A combustion system as recited in claim 11 , wherein the inner and outer cowls are mounted to the inner and outer combustor dome rings, respectively, with clips on the upstream and downstream sides of the combustor dome.

13 . A combustion system as recited in claim 12 , wherein the clips are proximate the fuel manifold to provide heat shielding to the fuel manifold.

14 . A combustion system as recited in claim 9 , wherein each of the inner and outer cowls forms a continuous shell devoid of support structures obstructing flow to the nozzles.

15 . A combustor for a gas turbine engine comprising:
an inner combustor wall; an outer combustor wall radially outboard of the inner combustor wall, wherein the inner and outer combustor walls define a combustion space therebetween with an upstream inlet and a downstream outlet; and and a combustor dome connecting between the inner and outer combustor walls, the combustor dome including a fuel manifold with an inlet and nozzle components of a plurality of nozzles circumferentially spaced around the combustor dome wherein the fuel manifold and nozzle components are integrated with the combustor dome for fluid communication from the inlet to the nozzle components.

Assignees

• Delavan Inc

Inventors

• Prociw Lev A

Classifications

• F23R3/30

  comprising fuel prevapourising devices · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F05D2230/53

  by integrally manufacturing a component, e.g. by milling from a billet or one piece construction · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23K5/06

  from a central source to a plurality of burners · CPC title