Abstract: The disclosure relates to a hockey stick comprising a shaft and a blade, the shaft including a top side, a bottom side, a front side, a back side, an upper end, a lower end, and a length extending between the upper end and the lower end, the shaft including a first straight section and a second section. The first section extends from the lower end of the shaft to the second section and the second section extends from the first section to the upper end of the shaft. The second section is disposed at an angle relative to the first section, the angle being defined generally along a plane extending from the top side of the shaft to the bottom side of the shaft, wherein the second section starts at about ½ to about ? of the length of the shaft from the lower end of the shaft.

Abstract: The disclosure relates to a hockey stick comprising a shaft and a blade, the shaft including a top side, a bottom side, a front side, a back side, an upper end, a lower end, and a length extending between the upper end and the lower end, the shaft including a first straight section and a second section. The first section extends from the lower end of the shaft to the second section and the second section extends from the first section to the upper end of the shaft. The second section is disposed at an angle relative to the first section, the angle being defined generally along a plane extending from the top side of the shaft to the bottom side of the shaft, wherein the second section starts at about ½ to about ? of the length of the shaft from the lower end of the shaft.

Abstract: Lean flameout upon ignition in a turbine system including a turbine wheel (10) driven by motive gases including gases of combustion from a combustor (20) may be avoided by locating an orifice (130) downstream of the servo/.DELTA.P valve (52) that controls fuel flow to the fuel inlet (22) of the combustor (20).

Abstract: An airframe power unit for producing a power output in accordance with the invention includes a combustor (16) having a fuel injector (58) which injects fuel into the combustor which is combusted to form a gas stream (18); a turbine (12) driven by the gas stream from the combustor for producing the power output; an air supply (20) for providing pressurized gas containing oxygen blown down from a storage vessel (22) to the combustor which is used in the combusting of the fuel; a valve (24) disposed in the gas supply which controls a rate of supply of gas to the combustor in response to the control signal applied to the valve to cause the turbine to operate with a constant operational characteristic; a control for providing at least one control value (P.sub.S and S.sub.