In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.

The inventions applicable to industrial gas turbines at power plant to minimize nitrogen oxides from gas turbine exhaust and maximizing gas turbine efficiency done by replacing the standard air filter system by oxygen filtration system (O) to allow oxygen only and substituting the nitrogen by high-pressure water HPW injected in compressor (C) last stages only. The one unit of oxygen to be injected by 4 units of HPW, since air contains 5 units 4 units of nitrogen and 1 unit of oxygen, the 5 units of oxygen are to be injected by 20 units of HPW required for the process. A heat exchanger to be installed at gas turbine exhaust duct to heat the HPW injected into compressor (C) last stages, which is to be mixed with HPW at ambient/atmospheric temperature to cool compressor air outlet temperature to targeted temperature as shown in FIG. 1. A control system is essential to control the process.

The inventions applicable to industrial gas turbines at power plant to minimize nitrogen oxides from gas turbine exhaust and maximizing gas turbine efficiency done by replacing the standard air filter system by oxygen filtration system (O) to allow oxygen only and substituting the nitrogen by high-pressure water HPW injected in compressor (C) last stages only. The one unit of oxygen to be injected by 4 units of HPW, since air contains 5 units 4 units of nitrogen and 1 unit of oxygen, the 5 units of oxygen are to be injected by 20 units of HPW required for the process. A heat exchanger to be installed at gas turbine exhaust duct to heat the HPW injected into compressor (C) last stages, which is to be mixed with HPW at ambient/atmospheric temperature to cool compressor air outlet temperature to targeted temperature as shown in FIG. 1. A control system is essential to control the process.

A gas turbine engine system includes a gas turbine engine including a compressor, combustor including a plurality of late lean fuel injectors supplied with secondary fuel; gas turbine, and wash system configured to be attached and in fluid communication with the late lean fuel injectors. The wash system includes a water source including water; first fluid source including a first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal gas turbine components; a mixing chamber in communication with the water source and first fluid source; a water pump to pump the water to the mixing chamber; a first fluid pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at the late lean fuel injectors while the gas turbine engine is on-line.

A gas turbine engine system includes a gas turbine engine including a compressor, combustor including a plurality of late lean fuel injectors supplied with secondary fuel; gas turbine, and wash system configured to be attached and in fluid communication with the late lean fuel injectors. The wash system includes a water source including water; first fluid source including a first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal gas turbine components; a mixing chamber in communication with the water source and first fluid source; a water pump to pump the water to the mixing chamber; a first fluid pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at the late lean fuel injectors while the gas turbine engine is on-line.

The present disclosure provides systems and methods for processing ammonia. The system may comprise one or more reactor modules configured to generate hydrogen from a source material comprising ammonia. The hydrogen generated by the one or more reactor modules may be used to provide additional heating of the reactor modules (e.g., via combustion of the hydrogen), or may be provided to one or more fuel cells for the generation of electrical energy.

Leveraging a turboexpander to provide additional functionality in compressed gas fueled systems is disclosed. The system includes a compressed gas storage device storing a compressed gas at a first pressure. A turboexpander operably coupled with the compressed gas storage device, the turboexpander comprising a turbine coupled with a drive shaft, the turboexpander to maintain the compressed gas below a threshold temperature limit as it controllably expands the compressed gas from the first pressure to the second pressure via an amount of work obtained from a rotation of the turbine and the drive shaft. A compressed gas receiving device to receive the compressed gas at the second pressure from the turboexpander and generate an amount of electrical energy from the compressed gas.