Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base; an inner conductor extending along an axis from the base to an end; a resistive heating element electrically connected to the end of the conductor; an outer conductor being electrically connected to the heating element, the outer conductor surrounding and extending axially along the inner conductor and forming a return electrical path, the outer conductor being radially spaced apart from the inner conductor by a gap, and an electrical insulator in the gap.

Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the igniter having a ventilation path extending from an inlet to an outlet, the inlet fluidly connectable to a spacing located between a casing and a combustor liner of the gas turbine engine, the outlet extending circumferentially around the glow plug heater rod and oriented axially relative to the axis, the outlet fluidly connectable to a combustion chamber of the gas turbine engine delimited by the combustor liner.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.

Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system mounted to an aircraft. The method comprises driving a first rotating propulsor from a first electric motor operatively connected to a generator, driving a second rotating propulsor from a second electric motor operatively connected to the generator, and driving a third rotating propulsor from a thermal engine, the thermal engine operatively connected to the generator and configured to drive the generator.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the sleeve having an inner surface spaced from the glow plug heater rod to provide a gap between the inner surface and the glow plug heater rod, the gap extending radially relative to said axis.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis to a rod end distal from the base, the glow plug heater rod sized such that that the rod end is exposed to a combustion chamber of the gas turbine engine when the base is connected to the casing.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a sleeve extending at least partially axially along the heater rod, the sleeve having an inner surface facing and spaced apart from the rod, the inner surface defining a pocket adjacent to the heater rod and having a radial depth relative to the axis.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the heater rod extending from the base along an axis and terminating in a rod end, a peripheral wall extending circumferentially around the rod end and having a distal end directed away from the base, a gap between the peripheral wall and the heater rod, the rod end being axially retracted relative the distal end of the peripheral wall.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a combustor liner plug extending circumferentially around the heater rod, the combustor liner plug being sized and configured to extend inside an aperture in a combustor liner of the gas turbine engine when the base is connected to the casing between the heater rod and a periphery of the aperture.

Abstract: There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

Abstract: A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a plurality of fins disposed circumferentially around the glow plug heater rod, the fins extending axially along at least a portion of the glow plug heater rod. A gas turbine engine including such an igniter is further disclosed.

Abstract: There is provided an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, the heater rod having a heating section extending axially between axially opposite ends of a heater contained within the heater rod, a heat spreader being in thermal conduction contact with the heating section of the heater rod and extending radially therefrom.

Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.

Abstract: Disclosed is a process for the electrochemical transformation of a compound to form a product, the process comprising (i) effecting the transformation in the presence of an electrolyte comprising at least one room temperature ionic liquid, wherein the ionic liquid is air-stable and moisture-stable, (ii) recovering the product, and optionally (iii) recovering the ionic liquid. The process can be used to effect the electrochemical transformation of a wide range of organic compounds.

Abstract: Disclosed is a process for the electrochemical transformation of a compound to form a product, the process comprising (i) effecting the transformation in the presence of an electrolyte comprising at least one room temperature ionic liquid, wherein the ionic liquid is air-stable and moisture-stable, (ii) recovering the product, and optionally (iii) recovering the ionic liquid. The process can be used to effect the electrochemical transformation of a wide range of organic compounds.

Abstract: Intermediates such as methyl 2,2-dimethyl-5-ethenyl-1,3-dioxane-5-carbonate useful to prepare antiviral compounds such as penciclovir and famciclovir are disclosed.

Abstract: A process for preparing purine derivatives, such as famciclovir and penciclovir, by reacting two intermediates and using a palladium(0) catalyst and a ligand. Intermediates useful in the process are also claimed.