A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

A damped anti-rotational system is provided comprising a pawl carrier having an axis of rotation, a pawl pivotably mounted to the pawl carrier on a pivot joint, the pawl having a contact portion and a counterweight portion, a stop pin axially disposed in the pawl carrier and configured to contact the contact portion of the pawl in response to radially inward movement of the pawl, wherein the stop pin is mounted to the pawl carrier at a forward portion of the stop pin and an aft portion of the stop pin, wherein a forward O ring is disposed on the forward portion of the stop pin and an aft O ring is disposed on the aft portion of the stop pin.

A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K.sub.1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K.sub.2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.

An electrical power generation system for a vehicle includes a prime mover, an electrical generator to generate electrical power and a gear box operably connected to the prime mover and the electrical generator to transfer rotational energy from the prime mover to the electrical generator. A braking mechanism is located at the gear box to selectably transfer rotational energy from the prime mover to the electrical generator for selective generation of electrical power. A method of electrical power generation for a vehicle includes generating rotational energy at a prime mover, transferring the rotational energy to an electrical power generator, generating electrical power via the rotational energy transfer to the electrical power generator, and periodically stopping and/or starting the transfer of rotational energy from the prime mover to the electrical power generator via a braking mechanism in operable communication with the electrical power generator.

A gas turbine assembly having a first shaft, a first compressor and a first turbine mounted on the first shaft, a combustor between the first compressor and the first turbine and a second shaft and a second turbine mounted on the second shaft, the second turbine having an inlet connected to an outlet of said first turbine. The gas turbine assembly further includes a third shaft on which an upstream compressor is mounted, the upstream compressor having an outlet which is connectable to an inlet of the first compressor.

A fan brake system for controlling an industrial fan system, the fan brake system including a fan brake having a brake pad movable on the fan brake to selectively engage the fan system. An actuator including a motor can be operable to cause the fan brake to perform a braking procedure on the fan system to resist rotational movement of the fan system. A controller can be communicated with the actuator, the controller operable to selectively cause the actuator and the fan brake to perform the braking procedure, wherein the controller is operable to monitor and control power being supplied to the motor of the actuator during the braking procedure to maintain a torque output of the motor according to a predetermined torque profile during the braking procedure.

The invention relates to a method for operating a multi-stage air compression system (1) comprising an electrically driven first compressor (1.1) and a second compressor (1.2) driven by a turbine (2), wherein the compressors (1.1, 1.2) are arranged in a supply air path (3) and the turbine (2) is arranged in an exhaust air path (4) of an air system for supplying air to a fuel cell stack (5). According to the invention, when the air compression system (1) is started, the air compressed by means of the first compressor (1.1) is supplied to the fuel cell stack (5) via a bypass (6) to bypass the second compressor (1.2) and the second compressor (1.2) is connected to the surrounding environment on both the inlet and outlet sides via at least one valve (7, 8) and/or a throttle valve (9).

The invention further relates to a multi-stage air compression system (1) as well as a fuel cell system having a multi-stage air compression system (1).

An assembly for an aircraft propulsion system includes an open propulsor rotor and a powertrain configured to receive power from a turbine and drive both the propulsor rotor and a compressor section at the same time in a first mode of operation. In a second mode of operation, a brake is applied that stops rotation of the propulsor rotor and the turbine power received by the powertrain drives only the compressor section. In the second mode, the propulsor rotor is stationary or otherwise undriven which effectively prevents rotation of the propulsor rotor. This reduces or eliminates safety risks to ground crews resulting from an open propulsor rotor actively rotating as the aircraft is on the ground.

An assembly for an aircraft propulsion system includes an open propulsor rotor and a powertrain configured to receive power from a turbine and drive both the propulsor rotor and a compressor section at the same time in a first mode of operation. In a second mode of operation, a brake is applied that stops rotation of the propulsor rotor and the turbine power received by the powertrain drives only the compressor section. In the second mode, the propulsor rotor is stationary or otherwise undriven which effectively prevents rotation of the propulsor rotor. This reduces or eliminates safety risks to ground crews resulting from an open propulsor rotor actively rotating as the aircraft is on the ground.

A suction enabled post shutdown combustor cooling and ventilation system including a pump fluidly coupled with a suction line, wherein the suction line is fluidly coupled with suction ports proximate a fuel system component near the combustor; a pump suction valve positioned in the suction line upstream of the pump; a pump discharge line fluidly coupled with the pump, an outlet fluidly coupled with the pump discharge line; and an engine core flow path fluidly coupled with the suction ports.