The invention concerns a method for manufacturing of a gas turbine engine component (37) comprising an outer ring structure (42, 47), an inner ring structure (41), and a plurality of circumferentially spaced elements (46, 46a, 46b) extending between the inner ring structure (41) and the outer ring structure (42), wherein a primary gas channel for axial gas flow is defined between the elements (46, 46a, 46b), and wherein the component (37) has an inlet side for gas entrance and an outlet side for gas outflow. The invention is characterized in that the method comprises the step of machining a one-piece metal blank as to form a one-piece part (47) comprising: a portion (46b) of each of said elements (46), wherein said portion (46b) relates to a portion of an extension length of the elements (46) between said ring structures (41, 42); and a ring-shaped member (42) that connects said element portions (46b) and that is intended to form part of one of the ring structures. The invention also concerns a gas turbine engine (1) comprising a component (37) manufactured according to the above method.

Disclosed is an offset rotational non-reciprocating-piston internal combustion engine in which an outer ring rotates on a one axis and an inner disk rotates on a second offset axis. Pistons are connected to the outer ring, while cylinders and other devices for operating the engine are mounted within an inner disk that rotates on a second axis that is offset from the axis of the outer ring. The inner disk and outer ring rotate together, such that the pistons create conditions of compression and explosive expansion within the cylinders without vibrating reciprocal piston motion. A unique fuel injection system is also disclosed that provides a variable fuel pressure that is created by centrifugal forces on the fuel. Because of the rotating inner disk and outer ring, advantages are taken of centrifugal force and gravity to distribute fuel, air, oil, high-voltage current, and cooling air in the engine.

A compound engine system including a Wankel engine having a recess defined in the peripheral wall of the rotor in each of the three rotating chambers, the recess having a volume of more than 5% of the displacement volume of the chambers. The expansion in the turbine section compensates for the relatively low expansion ratio of the rotary engine.

A compound engine system includes a rotary engine with rotating chambers, a compressor section in successive communication with the rotating chambers, and a turbine section in successive communication with the rotating chambers. The turbine section has an output shaft. The output shaft and the engine shaft are drivingly engaged to each other and wherein the turbine section has a power output corresponding to from 20% to 35% of a total power output of the compound engine system. A method of compounding power in a compound engine system is also discussed.

A compound engine system includes a rotary engine with rotating chambers, a compressor section in successive communication with the rotating chambers, and a turbine section in successive communication with the rotating chambers. The turbine section has an output shaft. The output shaft and the engine shaft are drivingly engaged to each other and wherein the turbine section has a power output corresponding to from 20% to 35% of a total power output of the compound engine system. A method of compounding power in a compound engine system is also discussed.

A compound engine system includes a rotary engine with rotating chambers, a compressor section in successive communication with the rotating chambers, and a turbine section in successive communication with the rotating chambers. The turbine section has an output shaft. The output shaft and the engine shaft are drivingly engaged to each other and wherein the turbine section has a power output corresponding to from 20% to 35% of a total power output of the compound engine system. A method of compounding power in a compound engine system is also discussed.

Disclosed is an offset rotational internal combustion engine in which an outer ring rotates on a one axis and an inner disk rotates on a second offset axis. Pistons are connected to the outer ring, while cylinders and other devices for operating the engine are mounted within an inner disk that rotates on a second axis that is offset from the axis of the outer ring. The inner disk and outer ring rotate together, such that the pistons create conditions of compression and explosive expansion within the cylinders without vibrating reciprocal piston motion. A unique fuel injection system is also disclosed that provides a variable fuel pressure that is created by centrifugal forces on the fuel. Because of the rotating inner disk and outer ring, advantages are taken of centrifugal force and gravity to distribute fuel, air, oil, high-voltage current, and cooling air in the engine.

A method of manufacturing a component for a gas turbine engine according to an exemplary aspect of the present disclosure includes forming the component with a first manufacturing technique to include a first cavity and a second cavity, and a microcircuit in fluid communication with the first cavity, the component including an outer wall and a ribbed portion or a bulged portion extending from the outer wall. The exemplary method includes forming a plunged hole with a second manufacturing technique different from the first manufacturing technique to intersect at least a portion of the microcircuit and extend into the ribbed portion or the bulged portion.

An engine assembly including an internal combustion engine, an oil cooler connected to the engine to receive heated oil and discharge cooled oil, and an engine cover mounted to the internal combustion engine and having an opening to receive the oil cooler therein.

An exemplary gas turbine engine component assembly includes, among other things, a case having a generally cylindrical outer surface. At least one synchronizing ring is received at least partially about the outer surface of the case. A plurality shims situated between an inner surface on the at least one synchronizing ring and the outer surface of the case at a plurality of shim locations are circumferentially spaced about the case outer surface. Each shim location includes at least one of the shims. A radial thickness of the shims at a first one of the shim locations is different than the radial thickness of the shims at a second one of the shim locations.