| Patent Number |
Title Of Patent |
Date Issued |
| 6915636 |
Dual fuel fin mixer secondary fuel nozzle |
July 12, 2005 |
| A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform inj |
| 6898937 |
Gas only fin mixer secondary fuel nozzle |
May 31, 2005 |
| A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. |
| 6857271 |
Secondary fuel nozzle with readily customizable pilot fuel flow rate |
February 22, 2005 |
| An improved secondary fuel distribution system having a readily adjustable premix pilot nozzle for use in a gas turbine combustor is disclosed. The secondary fuel nozzle assembly has a premix fuel nozzle comprising an annular tubular manifold and a premix pilot nozzle. Multiple embodimen |
| 5813611 |
Compact pressure balanced fulcrum-link nozzle |
September 29, 1998 |
| The C/D axisymmetrical exhaust nozzle for a gas turbine engine is designed to fit on the engine and STOVL aircraft and includes a combined load balancing piston/synchronization ring that is discretely attached to a fulcrum link for positioning the convergent and divergent flaps of the |
| 5782294 |
Cooled liner apparatus |
July 21, 1998 |
| A liner apparatus is provided which includes an inner wall, a plurality of fasteners extending out from the inner wall, an impingement sheet attached to the inner wall by the fasteners, apparatus for spacing the inner wall and the impingement sheet a distance apart, and apparatus for sea |
| 5080284 |
Cooling system for the trailing edge of a liner |
January 14, 1992 |
| Disclosed is a device for cooling the trailing edge segment of a liner on a convergent flap of a nozzle on a gas turbine engine. The trailing edge cooling device enhances the cooling of the liner without introducing turbulence into the coolant, thereby allowing the coolant to be used to |
| 5079912 |
Convergent side disk cooling system for a two-dimensional nozzle |
January 14, 1992 |
| Disclosed is an apparatus and a method for cooling a rotatable convergent side disk in a two-dimensional nozzle for a gas turbine engine, in which coolant is supplied and exhausted through concentric conduits, the cooling requirements of a liner assembly are reduced by use of a thermal b |
| 4747542 |
Nozzle flap edge cooling |
May 31, 1988 |
| A cooling arrangement for the trailing edge of a nozzle flap 18 has a trailing edge liner 30,54 and a baffle plate 32,55. Air from plenum 22 passes through openings 38,54 to cool the trailing edge liner. Expansion of the nozzle liner 18 causes abutment seal 52 to open, increasing cooling |
