Abstract: A system and method for controlling an internal combustion engine include determining oil responsiveness based on pressure variations associated with oil pump pulses in response to a stimulus, and controlling the engine based on the determined oil responsiveness. The stimulus may be a change in oil temperature, engine speed, or commanded pump pressure, for example. The system and method may also use the rate of change of mean oil pressure to determine the oil responsiveness or measure of oil viscosity. Oil responsiveness may be used to control hydraulic actuators, such as variable cam timing devices, or valve deactivation devices.

Abstract: The invention relates to an intake manifold (1) for a primary air system of an internal combustion engine, especially in a motor vehicle. The inventive intake manifold (1) comprises a pipe section (2) that is composed of at least two pipe parts (3, 4) which are produced as injection-molded parts and are joined to each other by means of a connection (12). Said connection (12) is formed by a material that is sprayed on or injected in the area of a dividing line (5) between the pipe parts (3, 4).

Abstract: Methods and systems are provided for monitoring cylinder valve deactivation in an engine operating with a plurality of cylinder valves. One example method comprises, sensing a plurality of cylinder valve positions of a plurality of cylinder valves; and combining the plurality of sensed positions to form a combined cylinder valve signal. The method may further include identifying valve degradation and differentiating valve degradation among the plurality of cylinder valves based on the combined cylinder valve signal and an expected value of the signal, and further based on a crank angle at which the expected value differs from the combined signal.

Abstract: A combustor for a gas turbine engine operates with high combustion efficiency, and low nitrous oxide emissions during engine operations. The combustor includes at least one trapped vortex cavity, a fuel delivery system including two fuel circuits, and a fuel spray bar assembly. A pilot fuel circuit supplies fuel to the trapped vortex cavity and a main fuel circuit supplies fuel to the combustor. The fuel spray bar assembly includes a spray bar and a heat shield. The spray bar is sized to fit within the heat shield. The heat shield includes aerodynamically-shaped upstream and downstream sides.

Abstract: A combustor for a gas turbine engine operates with high combustion efficiency, and low nitrous oxide emissions during engine operations. The combustor includes at least one trapped vortex cavity, a fuel delivery system including two fuel circuits, and a fuel spray bar assembly. A pilot fuel circuit supplies fuel to the trapped vortex cavity and a main fuel circuit supplies fuel to the combustor. The fuel spray bar assembly includes a spray bar and a heat shield. The spray bar is sized to fit within the heat shield. The heat shield includes aerodynamically-shaped upstream and downstream sides.

Abstract: A combustor for a gas turbine engine operates with high combustion efficiency, and low nitrous oxide emissions during engine operations. The combustor includes at least one trapped vortex cavity, a fuel delivery system including two fuel circuits, and a fuel spray bar assembly. A pilot fuel circuit supplies fuel to the trapped vortex cavity and a main fuel circuit supplies fuel to the combustor. The fuel spray bar assembly includes a spray bar and a heat shield. The spray bar is sized to fit within the heat shield. The heat shield includes aerodynamically-shaped upstream and downstream sides.

Abstract: A combustor for a gas turbine engine operates with high combustion efficiency, and low carbon monoxide and nitrous oxide emissions during low, intermediate, and high engine power operations. The combustor includes a fuel delivery system that includes at least two fuel stages, at least one trapped vortex cavity, and at least one mixer assembly radially inward from the trapped vortex cavity. The two fuel stages include a pilot fuel circuit that supplies fuel to the trapped vortex cavity through a fuel injector assembly and a main fuel circuit that also supplies fuel to the mixer assembly with the fuel injector assembly.

Abstract: A combustor for a gas turbine engine operates with high combustion efficiency, and low carbon monoxide and nitrous oxide emissions during low, intermediate, and high engine power operations. The combustor includes a fuel delivery system that includes at least two fuel stages, at least one trapped vortex cavity, and at least one mixer assembly radially inward from the trapped vortex cavity. The two fuel stages include a pilot fuel circuit that supplies fuel to the trapped vortex cavity through a fuel injector assembly and a main fuel circuit that also supplies fuel to the mixer assembly with the fuel injector assembly.

Abstract: A combustor for a gas turbine engine operates with high combustion efficiency, and low carbon monoxide and nitrous oxide emissions during low, intermediate, and high engine power operations. The combustor includes a fuel delivery system that includes at least two fuel stages, at least one trapped vortex cavity, and at least one mixer assembly radially inward from the trapped vortex cavity. The two fuel stages include a pilot fuel circuit that supplies fuel to the trapped vortex cavity through a fuel injector assembly and a main fuel circuit that also supplies fuel to the mixer assembly with the fuel injector assembly.