Azusa, CA, United States
Azusa, CA, United States

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Patent
Aerojet Rocketdyne | Date: 2017-02-15

A gas turbine engine includes a combustor which has at least one annular wall (40, 42) defining a combustion chamber (44) therein. The annular wall (40, 42) is formed by a circumferential array of panels (60) overlapping one with another to define a plurality of radial gaps (62) between respective adjacent two panels (60). The radial gaps (62) are configured in a spiral pattern and are in fluid communication with the combustion chamber (44) and a space outside the combustor to allow air surrounding the annular wall (40, 42) to enter the combustion chamber (44) via the radial gaps (62) for film cooling.


Patent
Aerojet Rocketdyne | Date: 2017-02-08

An auxiliary power unit (10) for an aircraft includes a rotary intermittent internal combustion engine (12), a turbine (26) having an inlet in fluid communication with an outlet of the engine (12), the turbine (26) compounded with the engine (12), a compressor (20) having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor (20) rotatable independently of the turbine (26), an electric motor (64) drivingly engaged to the compressor (20), and a transfer generator (76) drivingly engaged to the engine (12), the transfer generator (76) and the electric motor (64) being electrically connected to allow power transfer therebetween. The compressor (20) or an additional compressor (21) may be in fluid communication with the inlet of the engine (12).


Patent
Aerojet Rocketdyne | Date: 2017-04-05

A turbine exhaust case (TEC) (28) of a turbofan aeroengine includes a mixer (30) for mixing exhaust gases with a bypass air stream, the TEC (28) comprising an annular hub (36) and the mixer (30) surrounding the hub (36), and a plurality of deswirling struts (58) circumferentially spaced apart with respect to a central axis (34) of the TEC (28) and located entirely within an axial length of the mixer (30). The mixer (30) defines a trailing edge (44a) having one or more upstream-most locations thereof where the mixing of the exhausted gases and the bypass air stream begins to take place. The deswirling struts (58) each extend radially across the annular exhaust gas duct (40) and interconnect the mixer (30) and the hub (36), defining a trailing edge (62) positioned upstream of and axially spaced away from the one or more upstream-most locations of the trailing edge (44a) of the mixer (30).


Patent
Aerojet Rocketdyne | Date: 2017-02-08

A turboprop engine assembly (10) for an aircraft, including an internal combustion engine (12) having a liquid coolant system, an air duct (70) in fluid communication with an environment of the aircraft, a heat exchanger (66) received within the air duct (70) having coolant passages (66a) in fluid communication with the liquid coolant system and air passages (66b) in fluid communication with the air duct (70), and an exhaust duct (80) in fluid communication with an exhaust of the internal combustion engine (12). The exhaust duct (80) has an outlet (82) positioned within the air duct (70) downstream of the heat exchanger (66) and upstream of an outlet (72) of the air duct (70), the outlet (82) of the exhaust duct (80) spaced inwardly from a peripheral wall (70) of the air duct (70). In use, a flow of cooling air surrounds a flow of exhaust gases.


Patent
Aerojet Rocketdyne | Date: 2017-02-08

An auxiliary power unit (10) for an aircraft includes a rotary intermittent internal combustion engine (12) drivingly engaged to an engine shaft (16), a turbine section having an inlet in fluid communication with an outlet of the engine(s) (12), the turbine section including at least one turbine (22, 26) compounded with the engine shaft (16), and a compressor (20) having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct (72) for providing bleed air to the aircraft, the compressor (20) having a compressor rotor connected to a compressor shaft (24), the compressor shaft (24) drivingly engaged to the engine shaft (16). The driving engagement between the compressor shaft (24) and the engine shaft (16) is configurable to provide at least two alternate speed ratios between the compressor shaft (24) and the engine shaft (16).


A system and method for blade angle position feedback. The system comprises an annular member operatively connected to rotate with a propeller, a sensor fixedly mounted adjacent the annular member and configured for detecting a passage of each singularity as the annular member is rotated and axially displaced and for generating a sensor signal accordingly, the annular member and sensor configured for relative axial displacement between a first relative axial position and a second relative axial position respectively corresponding to the first and the second mode of operation, and a detection unit connected to the sensor for receiving the sensor signal therefrom, determining on the basis of the sensor signal a time interval elapsed between the passage of successive singularities, and computing from the time interval blade angle position.


Patent
Aerojet Rocketdyne | Date: 2017-02-22

An auxiliary power unit (10) for an aircraft, including an internal combustion engine (12) having a liquid coolant system, a generator (64) drivingly engaged to the internal combustion engine (12) and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine (12), a first heat exchanger (66) in fluid communication with the liquid coolant system of the internal combustion engine (12), a second heat exchanger (68) in fluid communication with the liquid coolant system of the generator (64), an exhaust duct (70) in fluid communication with air passages (66b, 68b) of the heat exchangers (66, 68), and a fan (78) received in the exhaust duct (70) and rotatable by the internal combustion engine (12) for driving a cooling air flow through the air passages (66b, 68b). The liquid coolant system of the engine (12) may be distinct from fuel and lubricating systems of the auxiliary power unit (10).


Patent
Aerojet Rocketdyne | Date: 2017-01-04

An auxiliary power unit (10) for an aircraft, having an engine core (12), a compressor (18) having an outlet (180) in fluid communication with the engine core inlet (120), a turbine section (20) in fluid communication with the engine core outlet (120), and an excess air duct (82) having a first end in fluid communication with the compressor outlet (180) and a second end in fluid communication with a turbine inlet (240) of the turbine section (20). The excess air duct (82) defines a flow path between the compressor outlet (180) and the turbine section (20) separate from the engine core (12). The auxiliary power unit may include a generator (14) in driving engagement with the engine core (12) to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.


An aircraft heating assembly (10) including an internal combustion engine (12) having a liquid coolant system distinct from any fuel and lubricating system of the engine (12) and including cooling passages (64) in the internal combustion engine (12) for circulating a liquid coolant from a coolant inlet (66) to a coolant outlet (68), a coolant circulation path (70) outside of the internal combustion engine (12) and in fluid communication with the coolant inlet (66) and the coolant outlet (68), and a heating element (76) in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path (70) extends through a heat exchanger (72) configured to remove a portion of a waste heat from the liquid coolant. The heating element (76) is in heat exchange relationship with the coolant circulation path (70) to receive another portion of the waste heat therefrom.


Patent
Aerojet Rocketdyne and Jivan | Date: 2017-04-12

An integrated mixer/TEC (25) having structural features that may be individually used or combined to achieve a robust and durable design.

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