Abstract: A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

Abstract: A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

Abstract: Described herein are systems, methods, and software to manage virtual local area network (VLANs) over multiple data centers. In one example, a method of managing a gateway at a first data center includes receiving, at a local manager, configuration information for a VLAN segment and a global VLAN segment identifier from a global manager of the data centers. The method further includes generating a global policy engine (GPE) data structure that associates the global VLAN segment identifier with a virtual network identifier (VNI) for the first data center and one or more policy rules, wherein the policy rules are derived from IP address prefix information provided from a second gateway, such as an edge gateway.

Abstract: One embodiment of the present invention is a system for controlling flow through a rotor. The system includes an inlet port in the rotor and an outlet port in the rotor. The outlet port is in fluid communication with the inlet port. A fixed orifice is disposed in at least one of the inlet or outlet ports. A variable orifice is disposed in at least one of the inlet or outlet ports in a separate location from the fixed orifice.

Abstract: A turbine bucket for use with a turbine engine. The turbine bucket includes a shank and a platform bordered by a forward edge and an aft edge that are coupled together by a pair of side edges, the forward edge upstream from the aft edge. The platform includes at least one interlock seal extending outward from at least one of the side edges and a mating groove defined in at least one of the side edges, the groove sized to receive the at least one interlock seal extending from an adjacent turbine bucket.

Abstract: A system for controlling flow through a rotor includes an inlet port in the rotor and an outlet port in the rotor. The outlet port is in fluid communication with the inlet port. A variable orifice is disposed in at least one of the inlet or outlet ports. A method for controlling flow through a rotor includes diverting a process fluid and flowing the diverted process fluid through a fluid passage in the rotor. The method further includes reducing the flow of the diverted process fluid through the fluid passage in the rotor.