Fuel spray nozzle comprising axially projecting air guiding element for a combustion chamber of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10808935-B2
Application number	US-201816141287-A
Country	US
Kind code	B2
Filing date	Sep 25, 2018
Priority date	Sep 28, 2017
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

A combustion chamber assembly group includes a nozzle providing a fuel-air mixture at a nozzle exit opening. An end of a fuel guiding channel is bordered at the nozzle exit opening by a flow-off edge located radially outside, and an air guiding element of an air guiding channel of the nozzle located radially outside projects with respect to this flow-off edge in the axial direction with respect to a nozzle longitudinal axis such that: a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element, and/or a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is ≤50°.

First claim

The invention claimed is:

1. A combustion chamber assembly group, comprising:
a burner seal that comprises a bearing section that extends along a nozzle longitudinal axis and has a passage opening, and
a nozzle for a non-staged combustion chamber of an engine that is positioned inside a passage hole of the bearing section for providing a fuel-air mixture at a nozzle exit opening of the nozzle, wherein the nozzle has a nozzle main body that comprises the nozzle exit opening and that extends along the nozzle longitudinal axis, and the nozzle main body further comprises at least the following:
an inner first air guiding channel that extends along the nozzle longitudinal axis for conveying air to the nozzle exit opening,
a fuel guiding channel for conveying fuel to the nozzle exit opening, which is located radially further outside with respect to the nozzle longitudinal axis as compared to the inner first air guiding channel, and
at least one further air guiding channel that is located radially outside with respect to the nozzle longitudinal axis with regard to the fuel guiding channel, wherein an air guiding element for guiding air flowing from the at least one further air guiding channel is provided at an end of the at least one further air guiding channel located in an area of the nozzle exit opening

wherein:
one end of the fuel guiding channel at the nozzle exit opening is bordered by a flow-off edge that is located radially outside of the fuel guiding channel and the air guiding element projects into an axial direction with respect to the nozzle longitudinal axis, such that at least one chosen from the following applies:
a first reference angle that is present between the nozzle longitudinal axis and a first straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element is less than or equal to 50°, and
a second reference angle that is present between the nozzle longitudinal axis and a second straight boundary line extending through the point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is less than or equal to 50°,

wherein the burner seal has a radially widening flow guiding element in the area of the nozzle exit opening and an inner shell surface of the radially widening flow guiding element extends at an end of the burner seal at an angle to the nozzle longitudinal axis that substantially corresponds to, or is identical to, the at least one chosen from the first reference angle and the second reference angle.

2. The combustion chamber assembly group according to claim 1 , wherein at least one chosen from the first straight boundary line and the second straight boundary line extends tangentially to the flow-off edge and tangentially to the air guiding element.

3. The combustion chamber assembly group according to claim 2 , wherein the air guiding element has a radially inward pointing bulge and the at least one chosen from the first straight boundary line and the second straight boundary line extends through a point at the air guiding element that is located behind the radially inward pointing bulge of the air guiding element in the axial direction.

4. The combustion chamber assembly group according to claim 1 , wherein the flow-off edge and the air guiding element abut at an outer shell surface of a virtual straight circular cone, with a cone point being located on the nozzle longitudinal axis and with an opening angle of the cone corresponding to twice the at least one chosen from the first reference angle and the second reference angle.

5. The combustion chamber assembly group according to claim 1 , wherein the at least one further air guiding channel includes two further air guiding channels that are radially displaced with respect to each other, wherein one of the two further air guiding channels that is provided with the air guiding element forms a radially outermost one of the two further air guiding channels.

6. The combustion chamber assembly group according to claim 1 , wherein, in the area of the nozzle exit opening, the burner seal forms an end that is substantially flush or is flush with a heat shield of the combustion chamber assembly group.

7. The combustion chamber assembly group according to claim claim 6 , wherein, in the area of the nozzle exit opening, the burner seal forms an end that projects beyond the heat shield of the combustion chamber assembly group in the axial direction by a length a, for which the following applies with regard to a wall thickness d of the projecting end: a≤1.5 d.

8. An engine with the combustion chamber assembly group according to claim 1 .

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Staufer Max
• Gerendas Miklos
• Eggels Ruud

Classifications

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title

• F23D2900/11101

  Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23D11/107

  at least one of both being subjected to a swirling motion · CPC title