Fuel delivery system with a cavity coupled fuel injector

Abstract

A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.

What is claimed is: 
     
         1 . A fuel injection system for a gas turbine engine, comprising:
 a fuel delivery conduit;   a nozzle block comprising a nozzle aperture with a first cross sectional area; and   a cavity block comprising an airflow aperture and a cavity with a second cross sectional area that is greater than the first cross sectional area;   wherein the nozzle aperture injects fuel received from the fuel delivery conduit into the cavity, and the airflow aperture directs air to the cavity that mixes with the injected fuel; and   wherein the cavity comprises an elongated cross sectional geometry.   
     
     
         2 . The system of  claim 1 , wherein the cavity extends from a first cavity end that is adjacent to the nozzle block to a second cavity end, and wherein the first cavity end comprises the second cross sectional area, and the second cavity end comprises a third cross sectional area that is greater than the second cross sectional area. 
     
     
         3 . The system of  claim 1 , wherein the cavity extends from a first cavity end that is adjacent to the nozzle block to a second cavity end, and wherein the first cavity end comprises the second cross sectional area, and the second cavity end comprises a third cross sectional area that is greater than the first cross sectional area and less than the second cross sectional area. 
     
     
         4 . A fuel injection system for a gas turbine engine, comprising:
 a gas path wall comprising a wall aperture extending therethrough;   a nozzle block comprising a nozzle aperture with a first cross sectional area; and   a cavity block comprising a cavity with an elongated cross sectional geometry and a second cross sectional area that is greater than the first cross sectional area;   wherein the nozzle aperture injects fuel received from a fuel delivery conduit through the cavity and the wall aperture.   
     
     
         5 . The system of  claim 4 , wherein the cavity block further comprises an airflow aperture that directs cooling air to the cavity that mixes with the injected fuel. 
     
     
         6 . The system of  claim 4 , further comprising a biasing element that engages the cavity block with the gas path wall, wherein the cavity block further comprises a cavity aperture into which at least a portion of the nozzle block extends, and the cavity is defined within the cavity aperture adjacent to the nozzle block. 
     
     
         7 . A fuel injection system for a gas turbine engine, comprising:
 a fuel delivery conduit;   a nozzle block comprising a nozzle aperture with a first cross sectional area; and   a cavity block comprising an airflow aperture and a cavity with a second cross sectional area that is greater than the first cross sectional area;   wherein the nozzle aperture injects fuel received from the fuel delivery conduit into the cavity, and the airflow aperture directs air to the cavity that mixes with the injected fuel; and   wherein the cavity extends from a first cavity end that is adjacent to the nozzle block to a second cavity end, and wherein the first cavity end comprises the second cross sectional area, and the second cavity end comprises a third cross sectional area that is greater than the second cross sectional area.   
     
     
         8 . The system of  claim 7 , wherein the cavity comprises an elongated cross sectional geometry.