Tangential entry fuel nozzle

• US 5,461,865 A
• Filed: 02/24/1994
• Issued: 10/31/1995
• Est. Priority Date: 02/24/1994
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: McVey, John B., Snyder, Timothy S., Rosfjord, Thomas J., Hu, Aaron S., Schlein, Barry C.
• Primary Examiner(s): Thorpe, Timothy S.
• Application Number:
  US08/201,310
• Time in Patent Office: 614 Days
• Field of Search: 60/737, 60/742, 60/743, 60/748, 60/39.463, 431/12, 431/352, 431/353, 239/400, 239/403, 239/432, 239/434, 239/470, 239/504
• US Class Current: 60/737
• CPC Class Codes: F23C 2900/07002 Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
• CPC Class Codes: F23C 7/002 the air being submitted to a rotary or spinning motion cyclonic combustion chamber F23C3/006
• CPC Class Codes: F23D 17/002 gaseous or liquid fuel
• CPC Class Codes: F23D 2206/10 Turbines
• CPC Class Codes: F23R 3/12 inducing a vortex

Abstract

A premix liquid fuel nozzle has longitudinal air entrance slots (24) into a cylindrical chamber (20). A centerbody (42) produces an axially increasing flow area toward the chamber outlet (32). Liquid fuel is atomized in a specified location (58) adjacent the conical centerbody (42). This area has a high axial shear velocity producing thorough vaporization and uniform mixing before combustion.

Claims

1. A low NOx burner for a gas turbine engine, comprising:

a substantially cylindrical burner chamber having an axis, having an axially extending chamber wall, and having an upstream end and an outlet end;

said outlet end having a diameter "D";

at least one longitudinally extending slot in the wall of said cylindrical chamber, said slot having an axial length and a slot wall tangential to said chamber wall;

supply means for supplying air through said slot;

a gas distribution manifold located adjacent said slot and having a plurality of axially spaced openings for delivering gas into the airflow as it passes into said slot;

a conical body located in said chamber on the axis of said chamber with the base of said conical body at the upstream end of said chamber and the apex of said conical body toward the outlet end of said chamber;

an injection zone defined as an annular volume concentric with said conical body bounded by imaginary surfaces at 30% and 80% of the distance from said conical body surface to the diameter "D", and by planes axially located from the axial center of said inlet slot a distance 10% toward said base and 20% toward said outlet end of said inlet slot axial length; and

liquid fuel injection means for atomizing fuel within said injection zone.

2. A low NOx burner for a gas turbine engine as in claim 1 wherein:

said liquid fuel injection means comprises a splash plate located with at least a portion of said plate within said injection zone; and

means for directing a flow of liquid fuel against said splash plate.

3. A low NOx burner for a gas turbine engine as in claim 1 wherein:

said liquid fuel injection means comprises a plurality of imperforate fuel tubes terminating in said injection zone; and

a spray nozzle at the end of each fuel tube.

4. A low NOx burner for a gas turbine engine as in claim 1 comprising also:

said substantially cylindrical chamber formed of a plurality of partial cylinders having the axis of each cylinder offset from the axis of the other, whereby a plurality of slots are formed between the walls of adjoining partial cylinders.

5. A low NOx burner for a gas turbine engine as in claim 2 comprising also:

the number of partial cylinders and the number of slots being two.

6. A low NOx burner for a gas turbine engine, comprising:

a substantially cylindrical burner chamber having an axis, having an axially extending chamber wall, and having an upstream end and an outlet end;

said outlet end having a diameter "D";

at least one longitudinally extending slot in the wall of said cylindrical chamber, said slot having an axial length and a slot wall tangential to said chamber wall;

supply means for supplying air through said slot;

a gas distribution manifold for delivering gas into the airflow passing through said slot;

a centerbody located in said chamber on the axis of said chamber in a manner to increase the annular flow area around said centerbody toward said outlet end of said chamber;

an injection zone defined as an annular volume concentric with said centerbody bounded by imaginary surfaces at 30% and 80% of the distance from said centerbody surface to the diameter "D", and by planes axially located from the axial center of said inlet slot a distance 10% toward said base and 20% toward said outlet end of said inlet slot axial length; and

liquid fuel injection means for atomizing fuel within said injection zone.

7. A low NOx burner for a gas turbine engine as in claim 6 comprising also:

said substantially cylindrical chamber formed of two partial cylinders, having the axis of each cylinder offset from the axis of the other, whereby two slots are formed between the walls of adjoining partial cylinders.

8. A low NOx burner for a gas turbine engine, comprising:

a substantially cylindrical burner chamber having an axis, having an axially extending chamber wall, and having an upstream end and an outlet end;

said outlet end having a diameter "D";

at least one longitudinally extending slot in the wall of said cylindrical chamber, said slot having an axial length and a slot wall tangential to said chamber wall;

supply means for supplying air through said slot;

a centerbody tapered from a base to an apex, and located in said chamber on the axis of said chamber with the base of said centerbody at the upstream end of said chamber and the apex of said centerbody toward the outlet end of said chamber;

an injection zone defined as an annular volume concentric with said centerbody bounded by imaginary surfaces at 30% and 80% of the distance from said centerbody surface to the diameter "D", and by planes axially located from the axial center of said inlet slot a distance 10% toward said base and 20% toward said outlet end of said inlet slot axial length; and

liquid fuel injection means for atomizing fuel within said injection zone.

9. A low NOx burner for a gas turbine engine, comprising:

a substantially cylindrical burner chamber having an axis, having an axially extending chamber wall, and having an upstream end and an outlet end;

said outlet end having a diameter "D";

at least one longitudinally extending slot in the wall of said cylindrical chamber, said slot having an axial length and a slot wall tangential to said chamber wall;

supply means for supplying air through said slot;

a centerbody located in said chamber on the axis of said chamber having a large diameter base of said centerbody at the upstream end of said chamber and having an apex of said centerbody toward the outlet end of said chamber;

an injection zone defined as an annular volume concentric with said centerbody bounded by imaginary surfaces at 30% and 80% of the distance from said centerbody surface to the diameter "D", and near the axial center of said inlet slot;

liquid fuel injection means for atomizing fuel within said injection zone.

10. A low NOx burner for a gas turbine engine as in claim 9 comprising also:

said substantially cylindrical chamber formed of two partial cylinders having the axis of each cylinder offset from the axis of the other, whereby two slots are formed between the walls of adjoining partial cylinders.

11. A method of burning liquid fuel in the combustor of a gas turbine engine with a premixing type of combustion, comprising:

tangentially introducing combustion air through a slot of length "L" into a substantially cylindrical chamber having a centerbody and increasing axial flow area toward an outlet end of said substantially cylindrical chamber having a diameter "D";

distributively atomizing liquid fuel into said combustion air in an injection zone in said substantially cylindrical chamber, said injection zone located from 10% of the length "L" upstream of the center of said slot to 20% of the length "L" downstream, and between 30% and 80% of the distance from said centerbody to said diameter "D"; and

burning said main gas flow at the outlet of said substantially cylindrical chamber.