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 computer implemented method and system for securing a virtual environment and virtual machines in the virtual environment is provided. A credential authority server is provided for managing environment credentials of the virtual environment. A virtual machine shim is associated with each of the virtual machines, and one or more hypervisor shims are associated with one or more hypervisors. The credential authority server provides, on request, environment credentials to each of the virtual machines and the hypervisors on authorization of each of the virtual machines and the hypervisors. Each virtual machine shim associated with each of the virtual machines communicates the provided environment credentials to the hypervisor shims for validation. The hypervisors associated with the hypervisor shims validate each of the virtual machines associated with each virtual machine shim based on the communicated environment credentials to allow instantiation of each of the virtual machines in the virtual environment.