Electrical power systems for distributing electrical power in aircraft are described. One such electrical power system comprises: an electrical power source configured to output a number R≥2 of dc power channels, each dc power channel having a respective index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein N>R and each dc load channel has a respective index n=(1, . . . , N). The system further comprises, for each respective one of a plurality of the N load channels, a current limiting device (CLD) operable to limit an amount of current flowing from the power channels to a load connectable to the electrical power system via the respective load channel. The electrical power source may comprise one or more batteries.

The combined cycle power device is provided in the present invention and belongs to the field of energy and power technology. A combined cycle power device comprising an expander, the second expander, a compressor, a pump, a high-temperature heat exchanger, a condenser and an evaporator. An evaporator connects the second expander after that a condenser passes through a pump and connects the evaporator. The second expander connects the high-temperature heat exchanger. A compressor connects the high-temperature heat exchanger. The high-temperature heat exchanger connects an expander. The evaporator connects the compressor and the condenser respectively after that the expander connects the evaporator. The high-temperature heat exchanger connects the outside. The condenser connects the outside. The evaporator connected the outside. The expander and the second expander connect the compressor and transmit power.

A metal catalytic converter system employs an engine having an exhaust duct. A multistage metal catalytic converter is mounted in the exhaust duct. A compressor stage is mounted in the exhaust duct, the compressor stage configured to reduce exhaust backpressure created by the converter.

A metal catalytic converter system employs an engine having an exhaust duct. A multistage metal catalytic converter is mounted in the exhaust duct. A compressor stage is mounted in the exhaust duct, the compressor stage configured to reduce exhaust backpressure created by the converter.

Electrical power systems for distributing electrical power in arrangements including one or more gas turbine engines; one such system includes: one or more rotary electric machines coupled to a gas turbine engine spool; a set of converter circuits connected to the rotary electric machines converting between alternating current (ac) and direct current (dc), wherein the rotary electric machines and the converter circuits output a number R≥2 of dc power channels, each channel having an index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein N>R and each dc load channel has an index n=(1, . . . , N). For each respective N load channels, a current limiting device (CLD) limits the current flowing from power channels to a load connectable to the electrical power system via the respective load channel.

Electrical power systems for distributing electrical power in arrangements including one or more gas turbine engines; one such system includes: one or more rotary electric machines coupled to a gas turbine engine spool; a set of converter circuits connected to the rotary electric machines converting between alternating current (ac) and direct current (dc), wherein the rotary electric machines and the converter circuits output a number R≥2 of dc power channels, each channel having an index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein N>R and each dc load channel has an index n=(1, . . . , N). For each respective N load channels, a current limiting device (CLD) limits the current flowing from power channels to a load connectable to the electrical power system via the respective load channel.

In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.

In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.

A gas turbine engine exhaust system comprises an instrumented exhaust duct including a set of exhaust temperature probes installed at the exhaust end of the duct in an air space between the engine outer case and a surrounding engine nacelle. A shield is removably installed at the end of the exhaust duct to protect the probes and associated wiring in the air space.

A power plant with a multi-stage intercooled compressor, a combustion chamber, a turbine which is arranged downstream of the combustion chamber, a compressor air line which connects the compressor to the combustion chamber, and a first heat exchanger which is connected into the compressor air line and into an exhaust gas line branching off from the turbine. A first compressor air expander is arranged in the compressor air line between the first heat exchanger and the combustion chamber, and the power plant includes a device for regasifying liquid natural gas, having a natural gas line, wherein a heat exchanger device is connected into the natural gas line between two compressor stages of the compressor.