Pressure regulators together with associated methods and systems are provided. An embodiment of a pressure regulator includes a chamber having an inlet port for receiving a fluid and an outlet port for delivering the fluid at a regulated pressure. The pressure regulator includes a diaphragm defining at least part of the chamber, and the diaphragm defining a first orifice therethrough. The pressure regulator includes a spring configured to interact with the diaphragm. The pressure regulator includes an interface operatively disposed between the spring and the diaphragm. The interface includes a contact surface for contacting the diaphragm, and the contact surface is convex toward the diaphragm. The interface defines a second orifice therethrough that is in fluid communication with the first orifice in the diaphragm. The first and second orifices define a relief port for venting the chamber to an ambient environment external to the chamber.

An air intake scoop intended to be fastened on a panel of an aircraft includes an air inlet mouth having a wall, a peripheral collar intended to be fastened to the panel, and a bearing element intended to support the air circulation duct. The air inlet mouth is made of a thermoplastic material and the bearing element is fastened on the peripheral collar so as to achieve a pressure barrier in case of breakage of the wall of the air inlet mouth.

A gas turbine engine includes a first spool associated with a diffuser and a primary combustor and a second spool associated with a secondary combustor. The first spool includes a first compressor and a first turbine mounted to a first shaft, and the second spool includes a second compressor and a second turbine mounted to a second shaft. An inlet duct fluidly connects the diffuser to the second compressor. An outlet duct assembly fluidly connects the second turbine to the diffuser and the primary combustor.

A gas turbine engine includes a first spool associated with a diffuser and a primary combustor and a second spool associated with a secondary combustor. The first spool includes a first compressor and a first turbine mounted to a first shaft, and the second spool includes a second compressor and a second turbine mounted to a second shaft. An inlet duct fluidly connects the diffuser to the second compressor. An outlet duct assembly fluidly connects the second turbine to the diffuser and the primary combustor.

A method for energy conversion for a vehicle is provided. The method including extracting a flow of compressed fluid from a compressor section of a propulsion system; flowing the flow of compressed fluid to a turbine operably coupled to a driveshaft, in which the driveshaft is operably coupled to a load device; expanding the flow of compressed fluid through the turbine to generate an output torque at the driveshaft to operate the load device; and flowing the expanded flow of compressed fluid from the turbine to thermal communication with a thermal load.

A method for energy conversion for a vehicle is provided. The method including extracting a flow of compressed fluid from a compressor section of a propulsion system; flowing the flow of compressed fluid to a turbine operably coupled to a driveshaft, in which the driveshaft is operably coupled to a load device; expanding the flow of compressed fluid through the turbine to generate an output torque at the driveshaft to operate the load device; and flowing the expanded flow of compressed fluid from the turbine to thermal communication with a thermal load.

Methods and systems for determining an engine temperature for a gas turbine engine are provided. An estimated combustor temperature is determined based on at least one operating condition of the gas turbine engine and an estimated vane mass flow. A corrected vane mass flow is determined based on the estimated combustor temperature, the estimated vane mass flow, and a combustor pressure. The corrected vane mass flow is compared to a reference vane mass flow to obtain the mass flow correction factor. When a condition associated with the mass flow correction factor is not satisfied, the estimated combustor temperature is adjusted based on the mass flow correction factor to produce an adjusted combustor temperature; and the mass flow correction factor is updated based on the adjusted combustor temperature. When the condition associated with the mass flow correction factor is satisfied, the estimated combustor temperature is assigned as the engine temperature.

Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.

Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.

A hybrid electric engine including a gas turbine engine including a low speed spool, a high speed spool a fan section, a compressor section, a combustor section, and a turbine section. The hybrid electric engine further includes an electric generator configured to convert rotational power of the high or low speed spool to electricity and a variable area turbine control system electrically connected to the electric generator. The variable area turbine control system being configured to adjust a cross-sectional area of a core flow path of the hybrid electric engine. The variable area turbine control system including a plurality of variable turbine vanes located in the turbine section and a variable area turbine actuator configured to rotate each of the plurality of variable turbine vanes to adjust the cross-sectional area of the core flow path of the hybrid electric engine. The variable area turbine actuator is an electromechanical actuator.