Michael W Sledd

US Patent:

50976664, Mar 24, 1992

Filed:

Dec 11, 1989

Appl. No.:

7/448541

Inventors:

Jack R. Shekleton - San Diego CA
Michael W. Sledd - Vista CA
Steven S. Sachrison - LaJolla CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F23R 330

US Classification:

60737

Abstract:

In order to achieve ignition at altitude, particularly in relatively small combustors (10) with low fuel flow rates, a fuel injection system (20) includes an air nozzle (26), a fuel nozzle (28), and an air assist tube (34). The fuel nozzle (28) is disposed in a manner so as to direct fuel through the air nozzle (26) and includes a fuel metering orifice (30) or capillary tube (32) to control fuel flow therethrough. The air assist tube (34) is integrally associated with the fuel nozzle (28) downstream of the fuel metering orifice (30) or capillary tube (32) to accelerate fuel flowing through the fuel nozzle (28). With this arrangement, the air nozzle (26) may comprise an opening in a combustor wall (14) defining a combustion chamber (12) of a turbine engine combustor (10) wherein a combustor case (16) surrounds the combustor wall (14) to define an air flow path 18 in communication with a compressed air source whereby compressed air flows through the opening (26) and into the combustor (10) along with fuel from the fuel nozzle (28) and air from the air assist tube (34).

US Patent:

53219503, Jun 21, 1994

Filed:

Oct 9, 1991

Appl. No.:

7/773549

Inventors:

Jack R. Shekleton - San Diego CA
Michael W. Sledd - Vista CA
Steven A. Sachrison - LaJolla CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F02C 722

US Classification:

60740

Abstract:

In order to achieve ignition at altitude, particularly in relatively small combustors (10) with low fuel flow rates, a fuel injection system (20) includes an air nozzle (26), a fuel nozzle (28), and an air assist tube (34). The fuel nozzle (28) is disposed in a manner so as to direct fuel through the air nozzle (26) and includes a fuel metering orifice (30) or capillary tube (32) to control fuel flow therethrough. The air assist tube (34) is integrally associated with the fuel nozzle (28) downstream of the fuel metering orifice (30) or capillary tube (32) to accelerate fuel flowing through the fuel nozzle (28). With this arrangement, the air nozzle (26) may comprise an opening in a combustor wall (14) defining a combustion chamber (12) of a turbine engine combustor (10) wherein a combustor case (16) surrounds the combustor wall (14) to define an air flow path 18 in communication with a compressed air source whereby compressed air flows through the opening (26) and into the combustor (10) along with fuel from the fuel nozzle (28) and air from the air assist tube (34).

US Patent:

50637452, Nov 12, 1991

Filed:

Jul 13, 1989

Appl. No.:

7/379548

Inventors:

Jack R. Shekleton - San Diego CA
Steven A. Sachrison - LaJolla CA
Michael W. Sledd - Vista CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F02C 100

US Classification:

60737

Abstract:

Improved fuel atomization for turbine engines operating at low fuel flows and at high altitudes is accomplished in an engine 10 having an annular combustor 12 by utilizing fuel injectors 18 provided with fuel supply tubes 24 disposed within air tubes 20 wherein the fuel supply tubes 24 each have an exit orifice 26 internally of the corresponding air tube 20 and upstream of an exit orifice 22 thereof with a fuel impingement surface 28 being provided within the air tube 20 in confronting relation to the exit orifice 26 of the fuel supply tube 24 to produce a conical fuel film 36 subjected to pressurized air to enhance fuel atomization.

US Patent:

52207943, Jun 22, 1993

Filed:

Jun 22, 1990

Appl. No.:

7/542739

Inventors:

Michael W. Sledd - Vista CA
Jack R. Shekleton - San Diego CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F23R 320

US Classification:

60737

Abstract:

The high cost of fuel injection nozzles for a gas turbine engine may be reduced by utilizing nozzles (60) formed of simple tubes (63) of capillary cross section having an integral flange (62) formed on one end (86) thereof.

US Patent:

53178645, Jun 7, 1994

Filed:

Sep 30, 1992

Appl. No.:

7/954971

Inventors:

Linn C. Shorb - San Diego CA
Michael W. Sledd - San Diego CA
Jack R. Shekleton - San Diego CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F23R 332
F02C 722

US Classification:

60 3936

Abstract:

Difficulties in downsizing annular combustors (20) due to orienting fuel injectors with respect to oxidant blast tubes are avoided in a construction for a combustor (20) including radially spaced annular walls (22, 24) and an interconnecting radial wall (26) defining an annular combustion chamber (32). A plurality of circumferentially spaced tubes (28, 30) extend through the radially outermost annular wall (24) and are directed generally tangentially into the combustion space (32). A plurality of fuel injectors (42) are provided for directing fuel radially inwardly into the space (32) and are circumferentially spaced about the combustion space (32) and located between the tubes (28).

US Patent:

51408074, Aug 25, 1992

Filed:

Feb 1, 1991

Appl. No.:

7/649478

Inventors:

Jack R. Shekleton - San Diego CA
Michael W. Sledd - Vista CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F23R 316
F23R 332

US Classification:

60 3936

Abstract:

Poor atomization of fuel at low fuel flows in a gas turbine engine may be overcome in an engine including a rotary compressor (14), a turbine wheel (22) coupled to the compressor (14) to drive the same and a nozzle of (26) for directing gases of combustion at the turbine wheel (22). An annular combustor (34) defines a combustion annulus about the turbine wheel (22) and has an outlet (30) connected to the nozzle (26). A plurality of air blast tubes (50) include exit openings (52) circumferentially spaced about the combustor (32) and each has an axis (54) that is generally circumferentially directed with respect to the combustion annulus. A fuel discharge orifice (64) is located within each air blast tube (50) and a flange (66) is aligned with each orifice (64) in the path of fuel being discharged therefrom and at a substantial acute angle (. theta. ) to the axis (54).

US Patent:

50276034, Jul 2, 1991

Filed:

Sep 14, 1990

Appl. No.:

7/583007

Inventors:

Jack R. Shekleton - San Diego CA
Steven A. Sachrison - La Jolla CA
Michael W. Sledd - Vista CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F02C 300

US Classification:

60743

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 start fuel injectors 46 provided with discharge orifices 56 and planar impingement surfaces 60 within the path of fuel discharged from the orifices 56 to provide flat sprays 62 that are generally tangential to the annular combustor 26 so as to be intercepted by an igniter 70 in a radial wall 34 of the combustor 26.

US Patent:

52770222, Jan 11, 1994

Filed:

Oct 23, 1992

Appl. No.:

7/966903

Inventors:

Jack R. Shekleton - San Diego CA
Michael W. Sledd - Vista CA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

F23R 332
F02C 722

US Classification:

60 3936

Abstract:

In order to enhance fuel injection efficiency, and particularly to atomize low fuel flows at high velocity with low fuel pressure, a fuel injection system 24 for a combustor 22 of a turbine engine 20 has an air blast tube 48 and a fuel supply tube 76. The air blast tube 48 is mounted at an acute angle relative to a wall 26 of the combustor 22 and has a first end 50 in communication with the combustor 22 and a second, enlarged end 52 disposed at an acute angle to an axis 54 of the air blast tube 48 in communication with a source of compressed air externally of the wall 26 of the combustor 22. The air blast tube 48 is operable to deliver compressed air from the source into the combustor 22. The fuel supply tube 76 delivers fuel through a fuel supply orifice 58 to a point at or near the first end 50 of the air blast tube 48 and has a first end 60 in communication with the combustor 22 through the fuel supply orifice 58 and a second end 62 in communication with a source of fuel externally of the wall 26 of the combustor 22. With this arrangement, the fuel supply tube 76 extends to a point communicating internally with the air blast tube 48 but adjacent a discharge opening 64 of the air blast tube 48 to produce an enhanced atomized fuel/air mixture thereby.