A muffler includes a housing defining a first chamber, a second chamber and a third chamber. The muffler includes at least a pair of nested protrusions in communication with an inlet. The pair of nested protrusions is coupled to a respective surface of a pair of plates disposed in the housing such that one of the pair of nested protrusions is spaced apart from and opposite another of the pair of nested protrusions to define a tortuous path that terminates at an outlet defined along an outer circumference. The first chamber is downstream from the pair of plates. The muffler includes a first tube fluidly coupled to the first chamber to direct the exhaust gases from the first chamber to the second chamber. The muffler includes a second tube fluidly coupled to the second chamber to direct the exhaust gases from the second chamber to the third chamber.

Provided is a rotating body, including: a shaft; and a compressor impeller including: a main body having an insertion hole, which extends from one end to another end side and is configured to receive the shaft inserted therethrough; a boss portion formed at one end side of the main body; and a joint portion, which is formed on an inner peripheral surface of the insertion hole at the boss portion and is welded to the shaft.

Provided is a rotating body, including: a shaft; and a compressor impeller including: a main body having an insertion hole, which extends from one end to another end side and is configured to receive the shaft inserted therethrough; a boss portion formed at one end side of the main body; and a joint portion, which is formed on an inner peripheral surface of the insertion hole at the boss portion and is welded to the shaft.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.

Aircraft power plants including combustion engines, and associated methods for recuperating waste heat from such aircraft power plants are described. A method includes transferring the heat rejected by the internal combustion engine to supercritical CO.sub.2 (sCO.sub.2) used as a working fluid in a heat engine. The heat engine converts at least some the heat transferred to the sCO.sub.2 to mechanical energy to perform useful work onboard the aircraft.

The present invention discloses embodiments for a power augmentation system of a gas turbine engine resulting in performance improvements while also improving efficiency. The invention provides systems and methods for generating a heated air supply by way of mixing compressed air from an electrically-driven process with air drawn from the engine compressor discharge plenum.

An engine assembly having an internal combustion engine, a turbine module including a turbine casing, a support casing rigidly connecting the turbine casing to a remainder of the assembly, and an inlet scroll connected to the turbine casing without any direct rigid connection to the support casing. The inlet scroll includes an inlet pipe for each engine exhaust port. An exhaust pipe is provided for each exhaust port, connected to and providing fluid communication between the respective exhaust port and inlet pipe. The exhaust pipe is movable relative to at least one of the exhaust port and the inlet pipe at a corresponding connection therewith. One of the exhaust and inlet pipes floatingly extends through an opening defined in the support casing. The assembly may be a compound engine assembly.

A turbine engine system utilizes one or more augmented combustion modules to produce an exhaust that is fed into the turbine portion of the engine and wherein power is produced by the augmented combustion module for use to drive the main shaft and/or for auxiliary purposes. An augmented combustion module is configured between the compressor and the turbine of the engine and receives compressed air from the compressor and ignites an air/fuel-mixture to turn a shaft that can be used to produce power. The shaft may be coupled with an electrical power generator, a pump, a hydraulic or pneumatic power generator and/or power conversion or transmission devices and/or coupled with the main shaft of the turbine engine. The power from a power generator may be stored in a battery, hydraulic accumulator or pneumatic accumulator and may be used to power auxiliary electrical, hydraulic or pneumatic devices.