An inertial particle separator includes a body with an outer wall, an inlet, an outlet, an inner nozzle, a settling chamber, a serpentine channel, and a filter element. The inlet is disposed on an upstream end of the body. The outlet is disposed on a downstream end of the body. The inner nozzle is disposed radially inward from the outer wall and forms a primary flow passage. The settling chamber is disposed in the body and extends between the outer wall and the inner nozzle. The settling chamber forms a secondary flow passage and is fluidly connected to the inlet and the outlet. The serpentine channel fluidly connects fluidly connects the inlet and the settling chamber and is disposed radially between the outer wall of the body and the inner nozzle. The filter element is disposed in the settling chamber.

A high efficiency reciprocating engine, nominally of the internal combustion type but alternatively of the external combustion type is disclosed. The new engine uses Hypocycloidal and alternatively Epicycloidal gear mechanisms to create differentiated compression and expansion ratios which then promote significant improvements in efficiency through lower compression losses and higher extraction of available energy. Through suitable augmentation, the engines can be made to provide higher power when needed over higher efficiency. Additionally, other parameter modifications enable realization of low side wall loads and true zero exhaust volume.

A high efficiency reciprocating engine, nominally of the internal combustion type but alternatively of the external combustion type is disclosed. The new engine uses Hypocycloidal and alternatively Epicycloidal gear mechanisms to create differentiated compression and expansion ratios which then promote significant improvements in efficiency through lower compression losses and higher extraction of available energy. Through suitable augmentation, the engines can be made to provide higher power when needed over higher efficiency. Additionally, other parameter modifications enable realization of low side wall loads and true zero exhaust volume.

A protection system for a turbo engine, in particular an aircraft engine is provided. The turbo engine comprises at least one fluid duct element with a casing device comprising at least one casing section, encasing at least partially the at least one fluid duct element, said casing device comprising at least one fluid escaping means, wherein the casing device is intended to at least partially contain and/or deflect a fluid stemming from a burst event at the fluid duct element event in order to at least partially protect the turbo engine.

A thermal mechanical dimple array for combustor liners of gas turbine engines are located at known hot spots along liner to reduce stress and minimize cracking. Such arrays have indentations in the liners at the hot spots that act to thermal mechanically flex the liner at the hot spot away from the heat source and distribute stresses such that cracking of the liner is reduced and durability is improved.

An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

Attaching a fastener to a ceramic matrix composite or ceramic body by inserting a portion of the fastener into a compartment of the body, the compartment having a first portion and a second portion, the second portion outboard of and narrower than the first portion; and delivering a fluid into the fastener to expand a portion of the fastener within the blind compartment first portion.

The present disclosure is directed to a sump housing for a gas turbine engine. The sump housing includes a base portion and a first wall extending outwardly from the base portion. The first wall and the base portion at least partially define an inner chamber. A second wall is positioned outwardly from the first wall and extends outwardly from the base portion. The base portion, the first wall, and the second wall at least partially define an outer chamber positioned outwardly from the inner chamber. A projection extending inwardly from the first wall engages a bearing assembly. The base portion, the first wall, the second wall, and the projection are integrally coupled together.

A double channel power turbine system includes an internal combustion engine body, a turbocharger and a mechanical driving device. The double channel power turbine includes a first power turbine channel with an inlet which is in connection with the internal combustion engine body after passing through an exhaust manifold, and a second power turbine channel with an inlet which is in connection with the internal combustion engine body after passing through the turbocharger turbine and the exhaust manifold; an outlet of each of the first power turbine channel and the second power turbine channel is in connection with an exhaust aftertreatment system; the exhaust gas discharged into the first power turbine channel and the exhaust gas in the second power turbine channel operate the double channel power turbine.

A reciprocating, internal combustion engine comprises a turbine connected to the exhaust port of a cylinder. The turbine receives exhaust gas from the cylinder and a power capture means transfers the power generated by the turbine to at least one of power storage device, a turbocharger, a compressor, and vehicle locomotion.