A radial centrifugal turbomachine with an adjusting device operatively active at the axial inlet of the turbomachine fixed casing, including: an annular member delimiting at least one radially inner passage at the axial inlet, wherein the member front surface and abutment surface of the casing delimit a radial annular passage. An actuator is connected to the member and to move axially and/or rotate according to a predefined angle to vary the radial annular passage and/or passage sections delimited between stator blades of the turbomachine first radial stage. A transmission shaft coaxial with the rotation axis and integral with the member is operatively connected to the actuator. The adjusting device allows adjusting the mass flow rate at the inlet to better adapt the performances of the turbomachine to the loading of the process/cycle and to implement a safety system dedicated to stopping the turbomachine in case of an urgent stop request.

An assembly is provided for a powerplant. This powerplant assembly includes a first powerplant structure, a second powerplant structure and a fuel injector bolt that fastens the second powerplant structure to the first powerplant structure. The fuel injector bolt includes an injector head and an injector base. The injector head longitudinally engages the second powerplant structure. The injector base projects longitudinally along a centerline out from the injector head, through a fastener aperture of the second powerplant structure and into an injector receptacle of the first powerplant structure. The injector base is attached to the first powerplant structure through a threaded interface.

A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air and also includes a toroidal recirculation zone configured to receive and combust fuel in a rich combustion zone, an ignitor positioned to ignite an air/fuel mixture in the rich combustion zone, a rapid quench zone downstream of the toroidal recirculation zone, a lean combustion zone downstream of the rapid quench zone, and a cooling air flow path configured to direct a second portion of the compressed air around an outer combustor liner.

A gas turbine engine includes a compressor configured to receive inlet air at a compressor inlet and generate compressed air at a compressor exit, a combustor positioned fluidically and physically downstream of the compressor, a turbine positioned fluidically and physically downstream of the combustor, and a shaft mechanically connecting the turbine and the compressor. The combustor is fluidically connected to the compressor to receive a first portion of the compressed air as combustor primary inlet air. The combustor includes a combustor liner having an inner combustor liner and an outer combustor liner, surrounding one or more combustion zones. A cooling air flow path is configured to direct a second portion of the compressed air around the outer combustor liner to cool the combustor liner and to provide a source of quench air, inner combustor liner cooling air, fuel injector air, and combustor secondary inlet air.

An assembly is provided for a powerplant. This powerplant assembly includes a first powerplant structure, a second powerplant structure and a fuel injector bolt that fastens the second powerplant structure to the first powerplant structure. The fuel injector bolt includes an injector head and an injector base. The injector head longitudinally engages the second powerplant structure. The injector base projects longitudinally along a centerline out from the injector head, through a fastener aperture of the second powerplant structure and into an injector receptacle of the first powerplant structure. The injector base is attached to the first powerplant structure through a threaded interface.

A disk engine and system configured to provide high power at a reduced axial length is disclosed herein. The disk engine includes a radial compressor, a compressor discharge manifold positioned circumferentially about compressor, a combustion chamber positioned within the discharge manifold and a radial turbine positioned radially inward of the combustion chamber.

An assembly for a turbine engine includes a nozzle structure, a septum and a plurality of cooling vanes. The nozzle structure includes a first platform, a second platform and a plurality of nozzle vanes arranged circumferentially about an axis. The septum axially and circumferentially overlaps the first platform with a cooling cavity formed by and radially between the septum and the first platform. The septum includes a plurality of cooling apertures aligned with the nozzle vanes. Each of the cooling apertures extends radially through the septum to the cooling cavity. The cooling cavity includes a cavity outlet fluidly coupled to a flowpath. The cooling vanes are arranged circumferentially about the axis and project from the first platform into the cooling cavity. The cooling vanes are located between the cooling apertures and the cavity outlet along the cooling cavity.