Fuel nozzle

Patent metadata

Field	Value
Publication number	US-10364988-B2
Application number	US-201715788092-A
Country	US
Kind code	B2
Filing date	Oct 19, 2017
Priority date	Sep 24, 2014
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine includes directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, filming the concentric two fuel flows on concentrically arranged inwardly facing filming surfaces that are disposed downstream of the flow splitter, and atomizing the concentric fuel flows into a core air flow.

First claim

The invention claimed is:

1. A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine, the method comprising:
directing a core air flow through a primary air passage of the fuel nozzle, the primary air passage extending centrally within the fuel nozzle and terminating at an exit located at a downstream end of the fuel nozzle;
directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, the flow splitter disposed downstream of the exit of the primary air passage;
filming the at least two concentric fuel flows on concentrically arranged and radially inwardly facing filming surfaces disposed downstream of the flow splitter; and
atomizing the at least two concentric fuel flows into the core air flow exiting the primary air passage.

2. The method of claim 1 , further comprising imparting a momentum to the pressurised fuel before filming the at least two concentric fuel flows; and
directing the fuel comprises directing a portion of the fuel toward the flow splitter by the action of a tangential component of a velocity of the fuel.

3. The method of claim 1 , wherein directing the fuel through the flow splitter comprises directing a portion of the fuel through a plurality of bifurcating passages disposed radially outwardly of a first fuel passageway and communicating with a second fuel passageway, the first fuel passageway include one of the filming surfaces and the second fuel passageway include the other one of the filming surfaces.

4. The method of claim 3 , further comprising forming the first and second fuel passageways to be annular.

5. The method of claim 1 , wherein the filming surfaces form a plurality of concentrically arranged nozzle tip projections disposed at the downstream end of the fuel nozzle.

6. The method of claim 1 , further comprising providing the filming surfaces radially outwardly of the primary air passage.

7. The method of claim 1 , further comprising forming the filming surfaces as frustoconical surfaces that converge radially toward a downstream annular edge of a tip of the fuel nozzle at the downstream end thereof.

8. The method of claim 1 , further comprising directing air through a secondary air passage concentrically defined radially outwardly of the primary air passage, the filming surfaces being disposed radially between the primary air passage and the secondary air passage.

Assignees

• Pratt & Whitney Canada

Inventors

• Hawie Eduardo David
• Davenport Nigel
• Wang Yen-Wen

Classifications

• F23D2900/11101

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

• F23R3/28 Primary

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

• F23D11/107

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

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title