Abstract: A method enables modeling of a gas turbine engine that includes a pulse detonation system. The method includes providing a pulse detonation modeling system, predicting characteristics of the engine using the pulse detonation modeling system, and predicting characteristics of the pulse detonation system using the pulse detonation modeling system.

Abstract: A heat exchange arrangement in an annular fan duct of a gas turbine engine includes a conduit routing hot bleed air flow, a heat exchanger disposed within the fan duct and connected with the conduit such that hot air is passed through the interior of the heat exchanger, and at least one and preferably a pair of partition members disposed within the fan duct for temporarily diverting a small portion of the main air flow from the fan duct and over the exterior of the heat exchanger in heat transfer relationship with the hot air passing through the interior of the heat exchanger. The small air flow portion rejoins the main air flow through the fan duct and is used to generate engine thrust after cooling the hot bleed air flow carried by the conduit. The partition members disposed adjacent to opposite sides of the heat exchanger and a support member define therewith an air diffusion passage through which the small fan duct air flow portion is diverted temporarily from the main fan duct air flow.