A fuel system for an aircraft includes a fuel source and a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path and stripping gas supply path are each in airflow communication with the fuel source.

An improved air scrubber has an improved, more efficient, more robust impeller and impeller housing for mixing incoming air with water, scrubbing the air with increased efficiency and lower mean time between failures. Also water flow through the system is improved to prevent loss of scrubbing performance and to reduce user workload. In addition to these improvements, the water intake system has been redesigned to use less water, prevent using too much water, and to prevent previously common errors that require users to drain water from the impeller housing.

A device for regulating the fuel supply flow rate for a turbine engine, comprising at least a pump, an upstream line leading to the pump, a downstream line downstream of the pump, a recirculation duct branched off the downstream line, allowing to collect the fluid in the downstream line and channel it towards the upstream line, a means for regulating the flow rate disposed on the recirculation duct, a phase measurer disposed in the upstream line, a computing unit connected to the phase measurer and to the flow rate regulating means, said computing unit controlling the flow rate regulating means such as to control the degree of opening of said flow rate regulating means, according to the gas content value in the upstream line.

A set screw (56) is provided, which has a screw main body (71), a male thread portion (75) which is formed on an outer periphery of the screw main body (71), and a drain hole (78) which penetrates a central portion of the screw main body (71) in an extension direction of the screw main body (71). The blade root ring (53) has a hole (63) which extends radially outward from an inner peripheral surface (53a) of the blade root ring (53), and a female thread portion (64) which is formed on an inner peripheral surface (63a) of the hole (63), and the set screw (56) is screwed into the female thread portion (64).

There is provided a turbine in which a sufficient measure against windage loss can be executed. In a turbine of an embodiment, a cooling medium higher in pressure and lower in temperature than a working medium is introduced to the inside from the outside of a turbine casing. Here, in at least a turbine stage of an exhaust stage, the cooling medium passes through a stator blade and thereafter passes through a flow path present between rotor blades and a rotor wheel to flow to an exhaust-stage wheel space.

There is provided an axial flow turbine capable of realizing a reduction in gland leakage amount. The axial flow turbine in an embodiment is of a single flow type and includes an upstream-side gland part located on an upstream side of a working medium in an axial direction of a turbine rotor and a downstream-side gland part located on a downstream side of the working medium in the axial direction of the turbine rotor. The axial flow turbine is configured such that a cooling medium lower in temperature and higher in pressure than the working medium is extracted in a middle of flowing from the inside to the outside of the turbine casing in the upstream-side gland part, and the extracted cooling medium is introduced into the stationary blade.

Oil lubrication systems for use on gas turbine engines are described. The systems include a conduit and an air/oil separator connected to and arranged along the conduit. The air/oil separator comprises includes a housing and a semi-permeable divider within the housing, the semi-permeable divider being permeable to air but not oil. The semi-permeable divider separates a first flow path of an air/oil mixture and a second flow path of low pressure such that air from the air/oil mixture passes through the semi-permeable divider and is removed from the air/oil mixture, and wherein an air-to-oil ratio is less at the second end of the first flow path as compared to the air-to-oil ratio at the first end of the first flow path.

A method of identifying the phase composition and/or changes in the phase composition of a fluid flowing through a turbomachine includes monitoring changes in at least one electrical parameter associated with operation of the turbomachine, and employing a known correlation between phase composition and or phase composition changes, and changes in the electrical parameter(s) to associate the monitored changes with changes in the actual phase composition of the fluid.

Provided are turbine engines and methods of operating thereof by heating and evaporating liquid fuels in a controlled manner prior to burning. Specifically, a fuel is heated and evaporated while avoiding coking. Coking is caused by pyrolysis when the fuel contacts a metal surface within a certain temperature range, which is referred herein to a coking temperature range. In the described methods, the fuel is transferred from one component, maintained below the coking temperature range, to another component, maintained above this range. The fuel is airborne and does not contact any metal surfaces during this transfer, and coking does not occur. In some examples, the fuel is also mixed with hot air during this transfer. The heated fuel, e.g., as an air-fuel mixture, is then supplied into a combustor, where more air is added to reach flammability conditions.

A fuel enhancement method and system for supplying the engine with a pressurized fuel mixture comprising a mixture of the liquid fuel and the gaseous component including provisions to maintain the ratio of gas to liquid in the mixture at a predetermined value and maintain the pressure of the fuel mixture applied to the engine at a predetermined value. A system using variable speed drive pumps is disclosed.