Abstract: A residue buffer, for temporary storage of portions of transmissions from a CPU to a graphics processor. Graphics commands are transmitted, in transmission units of uniform size, from a processor unit to an address generator, which processes the commands. The portion of the transmission unit not immediately usable by the graphics processor is stored in the residue buffer.

Abstract: In a computer graphics system, an address generator processes physical and virtual addresses using a common command set. A separate translator provides conversion from generated virtual addresses to physical addresses. The address generator formulates addresses as a function of distance from the origin of desired destination area in destination memory to the requested position in the destination area. A plurality of drawing graphics commands specify different raster drawing operations. A plurality of context graphics commands is used to define a desired context in which drawing graphics commands operate. The defined context includes destination location for resulting data, type and plane depth of graphics operations, foreground and/or background color of resulting data. Different parts of the context are changeable/redefinable independently of the other parts.

Abstract: In a computer graphics system, an address generator processes physical and virtual addresses using a common command set. A separate translator provides conversion from generated virtual addresses to physical addresses. The address generator formulates addresses as a function of distance from the origin of desired destination area in destination memory to the requested position in the destination area. A plurality of drawing graphics commands specify different raster drawing operations. A plurality of context graphics commands is used to define a desired context in which drawing graphics commands operate. The defined context includes destination location for resulting data, type and plane depth of graphics operations, foreground and/or background color of resulting data. Different parts of the context are changeable/redefinable independently of the other parts. The graphics commands have a format of multiple fields. Different fields specify different parameters.

Abstract: A liquid cooled stator blade assembly for a gas turbine engine includes an outer shroud having a pair of liquid inlets and a pair of liquid outlets supplied through a header and wherein means including tubes support the header radially outwardly of the shroud and also couple the header with the pair of liquid inlets and outlets.

Abstract: A gas turbine engine has an internal drive shaft including one end connected to a driven load and an opposite end connected to a turbine wheel and wherein the shaft has an in situ adjustable balance system near the critical center of a bearing span for the shaft including two 360.degree. rings piloted on the outer diameter of the shaft at a point accessible through an internal engine panel; each of the rings has a small amount of material removed from its periphery whereby both of the rings are precisely unbalanced an equivalent amount; the rings are locked circumferentially together by radial serrations thereon; numbered tangs on the outside diameter of each ring identify the circumferential location of unbalance once the rings are locked together; an aft ring of the pair of rings has a spline on its inside diameter that mates with a like spline on the shaft to lock the entire assembly together.

Abstract: A combustion liner for a gas turbine combustion apparatus is composed of a series of ceramic wall rings coaxially aligned from the upstream to the downstream end of the liner. The ceramic rings are connected so as to be free to expand radially relative to each other while maintaining alignment. One type of connection between the rings involves notches distributed around the ends of a ring and bosses distributed around the adjacent end of the next ring entering into the notches. Another type of interconnection involves notches distributed around adjacent ends of two ceramic rings with a metal ring disposed between them having bosses which engage in some of the notches to align the parts. The liner is supported by supports at the ends of the liner from an outer casing. One support includes a spring to accommodate relative expansion of the liner and outer casing.

Abstract: A combustion liner for a gas turbine combustion apparatus has a wall of ceramic material. To minimize destructive thermal gradients in the ceramic material due to local cooling by air entering the liner through ports for combustion or dilution air, the walls of these ports are isolated from the entering air by a lining for the port, either a coating applied to the wall of the port or a metal or ceramic sleeve extending through the port.

Abstract: A stationary annular rotor blade tip seal assembly includes an annular support extending continuously circumferentially around and radially outwardly of the tips of a plurality of blades on a turbine rotor. A seal mount ring includes a plural number of seal mount segments retained axially of the annular support and having circumferential ends on each of the adjacent segments spaced apart to receive a retaining spring and seal strip. A low density seal insert is mounted on each of the seal mount segments and is spring biased into seated engagement with each of the seal mount segments by the retaining spring with the seal strip closing a gap between each of the low density seal inserts.

Abstract: A combustion liner for a gas turbine combustion apparatus has a wall of ceramic material. To minimize destructive thermal gradients in the ceramic material due to local cooling by air entering the liner through ports for combustion or dilution air, the walls of these ports are isolated from the entering air by metal bushings inserted through each port, these bushings being retained by a band encircling the liner and connected to the bushings.