A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references.

A turbine engine assembly includes a core engine generating a high energy gas flow that is expanded through a turbine section, a hydrogen fuel system supplying hydrogen fuel to a combustor through a fuel flow path, a condenser extracting water from the high energy gas flow, an evaporator inputting thermal energy into the water extracted by the condenser to generate a steam flow, and at least one superheater receiving the steam flow from the evaporator and input thermal energy for heating the steam flow. The steam flow from the at least one superheater is injected into the core flow path upstream of the turbine section.

A turbine engine assembly includes a core engine generating a high energy gas flow that is expanded through a turbine section, a hydrogen fuel system supplying hydrogen fuel to a combustor through a fuel flow path, a condenser extracting water from the high energy gas flow, an evaporator inputting thermal energy into the water extracted by the condenser to generate a steam flow, and at least one superheater receiving the steam flow from the evaporator and input thermal energy for heating the steam flow. The steam flow from the at least one superheater is injected into the core flow path upstream of the turbine section.

A propeller control unit (PCU) for controlling pitch angles of blades of a propeller, has: a pitch angle actuator; a servo valve hydraulically connected to the pitch angle actuator and to a first hydraulic fluid source; and a feather valve having a body movable within a cavity, the feather valve having a first actuation port and a second actuation port both in fluid communication with the cavity, the body between the first actuation port and the second actuation port, the body being movable to selectively hydraulically connect the pitch angle actuator to the servo valve through the feather valve or to hydraulically connect the pitch angle actuator to a drain line through the feather valve, the first actuation port and the second actuation port hydraulically connected to a second hydraulic fluid source independent from the first hydraulic fluid source.

A propeller control unit (PCU) for controlling pitch angles of blades of a propeller, has: a pitch angle actuator; a servo valve hydraulically connected to the pitch angle actuator and to a first hydraulic fluid source; and a feather valve having a body movable within a cavity, the feather valve having a first actuation port and a second actuation port both in fluid communication with the cavity, the body between the first actuation port and the second actuation port, the body being movable to selectively hydraulically connect the pitch angle actuator to the servo valve through the feather valve or to hydraulically connect the pitch angle actuator to a drain line through the feather valve, the first actuation port and the second actuation port hydraulically connected to a second hydraulic fluid source independent from the first hydraulic fluid source.

1. Method, device and system for operating internal combustion engines with a considerably increased pressure ratio and vehicle with this system.

2.1 Internal combustion engines have a technically restricted pressure ratio, which limits the thermal efficiency. Gas turbines have so far had a maximum pressure ratio of 33:1, diesel engines have compression ratios of up to 23:1.

2.2 The oxidizer is fed into the combustion chamber in (cold) liquefied condition under very high pressure (1-2). The fuel is ideally also supplied in liquid form under high pressure. The pressure ratio of the oxidizer pump is 200, better 500 or more. In the combustion chamber, the oxidizer and fuel react with each other (2-3) and expand to far more than a thousand times the liquid volume. Depending on the fuel used, an expansion machine with a pressure ratio of around π=500 or more or an equivalent expansion ratio of ε=85 or more can be implemented (3-4).

2.3 The method enables the development of compact, cost-effective internal combustion engines with significantly increased efficiency, which are particularly suitable as vehicle propulsion systems.

1. Method, device and system for operating internal combustion engines with a considerably increased pressure ratio and vehicle with this system.

2.1 Internal combustion engines have a technically restricted pressure ratio, which limits the thermal efficiency. Gas turbines have so far had a maximum pressure ratio of 33:1, diesel engines have compression ratios of up to 23:1.

2.2 The oxidizer is fed into the combustion chamber in (cold) liquefied condition under very high pressure (1-2). The fuel is ideally also supplied in liquid form under high pressure. The pressure ratio of the oxidizer pump is 200, better 500 or more. In the combustion chamber, the oxidizer and fuel react with each other (2-3) and expand to far more than a thousand times the liquid volume. Depending on the fuel used, an expansion machine with a pressure ratio of around π=500 or more or an equivalent expansion ratio of ε=85 or more can be implemented (3-4).

2.3 The method enables the development of compact, cost-effective internal combustion engines with significantly increased efficiency, which are particularly suitable as vehicle propulsion systems.

In an aspect of the disclosure, a method, a computer-readable medium, and an apparatus are provided. The apparatus may be a vehicle power system, which includes an electric motor, a primary power source that energizes the electric motor, wherein the primary power source employs a turbine to generate electricity, a second power source that supplements the primary power source to energize the electric motor, and a control component that monitors power provided to the electric motor by the primary power source, that determines that additional power needs to be provided to the electric motor in order to meet a driving requirement, and that directs additional power from the second power source to the electric motor.

Various systems are provided for a charge-air cooler system. In one example, a system includes a turbocharger system having at least one compressor and one turbine and configured to provide charge air to an engine. The system also includes a charge-air cooler system having at least one charge-air cooler arranged below the at least one compressor, a turbocharger bracket arranged directly below the charge-air cooler system and shaped to mount the charge-air cooler and the turbocharger system to the engine, and a stator adapter physically coupling an alternator to the engine. The stator adapter includes an accessibility window arranged below the charge-air cooler system. The at least one charge-air cooler is closer to the accessibility window than the turbocharger system.

Various systems are provided for a charge-air cooler system. In one example, a system includes a turbocharger system having at least one compressor and one turbine and configured to provide charge air to an engine. The system also includes a charge-air cooler system having at least one charge-air cooler arranged below the at least one compressor, a turbocharger bracket arranged directly below the charge-air cooler system and shaped to mount the charge-air cooler and the turbocharger system to the engine, and a stator adapter physically coupling an alternator to the engine. The stator adapter includes an accessibility window arranged below the charge-air cooler system. The at least one charge-air cooler is closer to the accessibility window than the turbocharger system.