A shield member is disposed over a gap between platform portions of adjacent turbine rotor blades, made from a ceramic matrix composite, and configured to shield the gap between the platform portions.

A cooling system (10) positioned within a turbine airfoil (12) and having film cooling channels (16) positioned within inner and outer endwalls (18, 20) of the turbine airfoil (12), with cooling fluids supplied to the cooling channels (16) other than from an aft cooling chamber (22) to prevent blockages from developing within the film cooling channels (16) from debris that typically collects with the aft cooling chamber (22) during steady state operation of the turbine engine is disclosed. The cooling system (10) may include one or more midchord cooling channels (24) extending from a midchord cooling chamber (26) and including an outlet (28) positioned closer to a downstream edge (30) of the inner endwall (18) than an upstream wall (32) forming the aft cooling chamber (22). The midchord cooling channel, thus, may cool aspects of the inner endwall (18) radially outward of the aft cooling chamber (22) without receiving cooling fluid from aft cooling chamber (22), thereby eliminating the possibility of blockages from debris in the aft cooling chamber (22).

Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.

Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.

A gas turbine having a combustion chamber with exhaust section through which combustion gas is exhaustable, plenum chamber and compressor are provided. The plenum chamber is coupled to the compressor wherein a first quantity of compressed fluid is injectable therein at a radially inner wall of the plenum chamber. A guide vane section with at least one airfoil is coupled to the exhaust section so combustion gas is flowable against the airfoil. The exhaust section and guide vane section are housed inside the plenum chamber. The airfoil has a first flow chamber where a second quantity of compressed fluid is flowable through the guide vane section from the compressor in the direction from the inner wall to a outer wall of the plenum chamber before being discharged. The second quantity of compressed fluid streamable through the guide vane section is larger than the first quantity of the compressed fluid.

A gas turbine having a combustion chamber with exhaust section through which combustion gas is exhaustable, plenum chamber and compressor are provided. The plenum chamber is coupled to the compressor wherein a first quantity of compressed fluid is injectable therein at a radially inner wall of the plenum chamber. A guide vane section with at least one airfoil is coupled to the exhaust section so combustion gas is flowable against the airfoil. The exhaust section and guide vane section are housed inside the plenum chamber. The airfoil has a first flow chamber where a second quantity of compressed fluid is flowable through the guide vane section from the compressor in the direction from the inner wall to a outer wall of the plenum chamber before being discharged. The second quantity of compressed fluid streamable through the guide vane section is larger than the first quantity of the compressed fluid.

Method for operating a solar installation. The solar installation includes a solar field with direct evaporation accompanied by the generation of superheated live steam, a turbine for expanding the live steam, and a generator driven by the turbine for generating electrical energy. At least one valve is associated with the turbine by which the amount of live steam fed to the turbine is adjusted. The valve, or each valve, through which the amount of live steam fed to the turbine is adjusted such that an actual value of a live steam pressure occurring upstream of the turbine follows a reference value determined depending on a live steam temperature of the live steam upstream of the turbine.

Method for operating a solar installation. The solar installation includes a solar field with direct evaporation accompanied by the generation of superheated live steam, a turbine for expanding the live steam, and a generator driven by the turbine for generating electrical energy. At least one valve is associated with the turbine by which the amount of live steam fed to the turbine is adjusted. The valve, or each valve, through which the amount of live steam fed to the turbine is adjusted such that an actual value of a live steam pressure occurring upstream of the turbine follows a reference value determined depending on a live steam temperature of the live steam upstream of the turbine.

A sealing ring assembly for connection of an exhaust gas cooler to a coolant line may include a carrier ring composed of a plastic, a sealing ring composed of a sealing material connected to the carrier ring; and a heat protection element connected to the carrier ring and surrounding the carrier ring on a radial outer side defining an air gap therebetween.

A sealing ring assembly for connection of an exhaust gas cooler to a coolant line may include a carrier ring composed of a plastic, a sealing ring composed of a sealing material connected to the carrier ring; and a heat protection element connected to the carrier ring and surrounding the carrier ring on a radial outer side defining an air gap therebetween.