Abstract: Drive signals generated at a single location are utilized to derive localized clock signals at several locations. The drive signals are phase shifted and have identical frequencies, while the clock signals derived therefrom are some frequency multiple thereof.

Abstract: Inexpensive cooling of a gas turbine nozzle and shroud assembly 62, 66, 76 is obtained by locating passages 84, 88, 102 in the vanes 76 forming part of the nozzle structure 62, 66, 76 so as to open generally centrally of the vanes 76 in the area between the shrouds 62 and 66 and in the leading edge of the vanes 76.

Abstract: An annular combustor having radial dilution air injection in a gas turbine is disclosed. The gas turbine includes a rotor having turbine blades and a nozzle adjacent the turbine blades which is adapted to direct hot gases at the turbine blades to cause rotation of the rotor. The annular combustor is disposed about the rotor and has an outlet to the nozzle, spaced inner and outer walls, and a generally radially extending wall connecting the inner and outer walls. The gas turbine includes a housing substantially surrounding the annular combustor in spaced relation to the inner, outer and radially extending walls to define a dilution air flow path. The dilution air flow path includes a compressed air inlet in communication with a compressor supplying dilution air at one end thereof and a compressed air outlet in communication with the annular combustor adjacent the outlet at the other end thereof.

Abstract: The expense of fabricating an annular combustor for use with a small diameter gas turbine engine is minimized in a construction including a bell-shaped housing 52, an axially extending sleeve 66 within the housing 52, an annular liner 74 within the housing 52 and about the sleeve 66 and including inner, outer and radial walls 80, 76, 78, respectively, spaced from the sleeve 66 and the housing 52 and all being formed of sheet metal. A circular fuel manifold 108 with angularly spaced fuel dispensing openings 122 is disposed between the housing 52 and the outer wall 76 and a plurality of open ended, elongated tubes 112 extend through the outer wall 76 and are in fluid communication with respective openings 122 in the fuel manifold 108 to introduce air and fuel generally tangentially into the liner 74.

Abstract: The expense of fabricating an annular combustor for use with a small diameter gas turbine engine is minimized in a construction including a bell-shaped housing 52, an axially extending sleeve 66 within the housing 52, an annular liner 74 within the housing 52 and about the sleeve 66 and including inner, outer and radial walls 80, 76, 78, respectively, spaced from the sleeve 66 and the housing 52 and all being formed of sheet metal. A circular fuel manifold 108 with angularly spaced fuel dispensing openings 122 is disposed between the housing 52 and the outer wall 76 and a plurality of open ended, elongated tubes 112 extend through the outer wall 76 and are in fluid communication with respective openings 122 in the fuel manifold 108 to introduce air and fuel generally tangentially into the liner 74.