Patent application number | Description | Published |
20080260538 | Spar and shell constructed turbine blade - A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a tip portion extending in the spanwise direction and extending beyond the first wall and the second wall and a root portion extending longitudinally, an attachment portion having a central opening for receiving the foot portion and a platform portion. The root portion fits into the central opening and is secured therein by a pin extending transversely through the attachment and the foot portion. The shell fits over the spar and is supported thereto by a plurality of complementary hooks extending from the spar and, shell. The ends of the shell fit into grooves formed on the tip .portion and the platform, The shell is made from a high temperature resistant material, such as Molybdenum or Niobium, and is formed from a wife EDM process. | 10-23-2008 |
20090169395 | Tungsten shell for a spar and shell turbine vane - The present invention is a vane for us in a gas turbine engine, in which the vane is made of an exotic, high temperature material that is difficult to machine or cast. The vane includes a shell made from Tungsten, and is formed from a wire electric discharge process. The shell is positioned in grooves between the outer and inner shrouds, and includes a central passageway within the spar, and forms a cooling fluid passageway between the spar and the shell. Both the spar and the shell include cooling holes to carry cooling fluid from the central passageway to an outer surface of the vane for cooling. This cooling path eliminates a serpentine pathway, and therefore requires less pressure and less amounts of cooling fluid to cool the vane. | 07-02-2009 |
20090193657 | Process for forming a shell of a turbine airfoil - The present invention is a vane for us in a gas turbine engine, in which the vane is made of an exotic, high temperature material that is difficult to machine or cast. The vane includes a shell made from either Molybdenum, Niobium, alloys of Molybdenum or Niobium (Columbium), Oxide Ceramic Matrix Composite (CMC), or SiC-SiC ceramic matrix composite, and is formed from a wire electric discharge process. The shell is positioned in grooves between the outer and inner shrouds, and includes a central passageway within the spar, and forms a cooling fluid passageway between the spar and the shell. Both the spar and the shell include cooling holes to carry cooling fluid from the central passageway to an outer surface of the vane for cooling. This cooling path eliminates a serpentine pathway, and therefore requires less pressure and less amounts of cooling fluid to cool the vane. | 08-06-2009 |
20100229560 | Small gas turbine engine with multiple burn zones - A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor. | 09-16-2010 |
20100290917 | Spar and shell blade with segmented shell - A turbine rotor blade with a spar and shell construction, where the shell has an airfoil shape and is formed of two shell segments with an upper shell half and a lower shell half. The upper shell half is radially supported by a tip of the spar while the lower shell half is radially loaded by an attachment so that its load is not carried by the upper shell half and the tip of the spar in order to reduce overall stress levels. | 11-18-2010 |
20110020137 | Spar and shell constructed turbine blade - A blade for a rotor of a gas turbine engine is constructed with a spar and shell configuration. The spar is constructed in an integral unit or multi-portions and includes a first wall adjacent to the pressure side and a second wall adjacent to the suction side, a tip portion extending in the spanwise direction and extending beyond the first wall and the second wall and a root portion extending longitudinally, an attachment portion having a central opening for receiving the root portion and a platform portion. The root portion fits into the central opening and is secured therein by a pin extending transversely through the attachment and the root portion. The shell fits over the spar and is supported thereto by a plurality of complementary hooks extending from the spar and shell. The ends of the shell fit into grooves formed on the tip portion and the platform. The shell is made from a high temperature resistant material, such as Molybdenum or Niobium, and is formed from a wire EDM process. | 01-27-2011 |
20110305580 | Spar and shell blade with segmented shell - A turbine rotor blade with a spar and shell construction, where the shell has an airfoil shape and is formed of two shell segments with an upper shell half and a lower shell half. The upper shell half is radially supported by a tip of the spar while the lower shell half is radially loaded by an attachment so that its load is not carried by the upper shell half and the tip of the spar in order to reduce overall stress levels. | 12-15-2011 |
20120234016 | Small gas turbine engine with multiple burn zones - A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor. | 09-20-2012 |