Turbine engine with high efficiency fuel atomization

• US 4,989,404 A
• Filed: 12/12/1988
• Issued: 02/05/1991
• Est. Priority Date: 12/12/1988
• Status: Expired due to Fees

• Current Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Shekleton, Jack R.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): Thorpe, Timothy S.
• Application Number:
  US07/283,080
• Time in Patent Office: 785 Days
• Field of Search: 60/737, 60/738, 60/743, 60/34.826, 60/734, 60/39.36, 123/531, 239/424, 239/533.15
• US Class Current: 60/804
• CPC Class Codes: F02C 7/26 Starting; Ignition
• CPC Class Codes: F23R 3/28 characterised by the fuel supply burners F23D

Abstract

Improved fuel atomization for turbine engines operating at low fuel flows and at high altitudes is accomplished in an engine having an annular combustor 26 by utilizing fuel injectors 46 provided with radially inward discharge orifices 56 and planar impingement surfaces 60 within the path of fuel discharged from the orifices 56 to provide a flat spray 62 that is generally tangential to the annular combustor 26.

Claims

1. A gas turbine engine comprising:

a rotary compressor;

a turbine wheel coupled to said compressor to drive the same;

an annular nozzle proximate said turbine wheel for directing gases of combustion at said turbine wheel;

an annular combustor having inner and outer walls defining an annular combustion space disposed about said turbine wheel and in fluid communication with both said compressor and said nozzle, said combustor receiving fuel from a source and air from said compressor and combusting the same to generate said gases of combustion; and

at least one fuel injector for said combustor, said fuel injector extending through an outer wall, said fuel injector comprising at least one generally radially inwardly opening discharge orifice and a plate within said combustor in the path of fuel discharged from said orifice and at an angle thereto so as to cause said fuel to enter said annular combustion space generally circumferentially relative thereto.

2. The gas turbine engine of claim 1 wherein said fuel injector includes a barrel terminating in said discharge orifice and said plate is mounted on said barrel at an acute angle with respect to an end thereof and in spaced relation to said discharge orifice.

3. The gas turbine engine of claim 1 wherein said plate has generally planar impingement surface facing said discharge orifice.

4. A gas turbine engine comprising:

a rotary compressor;

a turbine wheel coupled to said compressor to drive the same;

an annular nozzle proximate said turbine wheel for directing gases of combustion to said turbine wheel;

an annular combustor having inner and outer walls defining an annular combustion space disposed about said turbine wheel and in fluid communication with both said compressor and said nozzle, said combustor receiving fuel from a source and air from said compressor and combusting the same to generate said gases of combustion; and

at least one fuel injector for said combustor, said fuel injector extending through an outer wall, said fuel injector comprising at least one generally radially inwardly opening discharge orifice and means defining an impingement surface within said combustor in the path of fuel discharged from said orifice and at an angle thereto so as to cause said fuel to enter said annular combustion space generally circumferentially thereto.

5. A gas turbine engine comprising:

a rotary compressor;

a turbine wheel coupled to said compressor to drive the same;

an annular nozzle proximate said turbine wheel for directing gases of combustion at said turbine wheel;

an annular combustor having inner and outer walls defining an annular combustion space disposed about said turbine wheel and in fluid communication with both said compressor and said nozzle, said combustor receiving fuel from a source and air from said compressor and combusting the same to generate said gases of combustion; and

at least one fuel injector for said combustor, said fuel injector extending through an outer wall said fuel injector comprising at least one inwardly opening discharge orifice and means defining an impingement surface within said combustor and spaced from said orifice while in the path of fuel discharged from said orifice and located so as to cause fuel discharged from said orifice to be in a flat spray generally circumferentially relative to said said annular combustion space.

6. The gas turbine engine of claim 5 wherein said orifice opens generally radially inwardly and said surface is generally planar.

7. The gas turbine engine of claim 5 wherein said turbine wheel defines a rotational axis and said surface is generally planar and parallel to said axis.

8. The gas turbine engine of claim 5 wherein said discharge orifice is a relatively short orifice to provide optimum atomization.