Lerg
Bryan H. Lerg, Westfield, IN US
Patent application number | Description | Published |
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20090288388 | Gas turbine exhaust - An exhaust device is disclosed that includes a duct that turns an exhaust flow from a gas turbine engine from a first direction to a second direction. A diverter cup is disposed within the duct and serves to split the exhaust flow into two streams as well as introduce cooling air through an ejector pump at the downstream end of the diverter cup. A splitter is disposed downstream of the diverter cup and serves to split the cooling air into two streams which are thereafter mixed with the split exhaust flow. A diffuser is created in the exhaust device between the duct and the splitter. Various cooling slots are also provided in the duct. | 11-26-2009 |
20100162682 | INLET PARTICLE SEPARATOR SYSTEM FOR A GAS TURBINE ENGINE - Embodiments include an inlet particle separator system for a gas turbine engine. The inlet particle separator system includes an inertial particle separator that separates incoming air into a cleaned air flow and a scavenge flow. Embodiments may also include an ejector that provides a draw on a scavenge duct and entrains the scavenge flow into a charged flow, e.g., such as the output of a first stage fan. The ejector may have a variable output. | 07-01-2010 |
20140263712 | EXHAUST NOZZLE APPARATUS AND METHOD FOR MULTI STREAM AIRCRAFT ENGINE - A multi stream aircraft fixed geometry nozzle includes an inner nozzle, an outer nozzle, and a supersonic ejector. The outer nozzle is configured to channel a third stream from an aft end of a third stream duct surrounding a bypass duct of a multi stream aircraft engine to the supersonic ejector to merge the third stream with the primary stream. The fixed geometry nozzle is configured to operate between an SFC mode and a thrust mode such that, when the inner nozzle accelerates the primary stream supersonically to the supersonic ejector, at which the primary stream is merged with the third stream, in the SFC mode the total pressure of the primary stream is substantially the same as the total pressure of the third stream, and in the thrust mode the total pressure of the primary stream is substantially greater than the total pressure of the third stream. | 09-18-2014 |
20150121840 | AIRCRAFT NOZZLE SYSTEM - A nozzle is provided that is capable providing flowpaths for a combined cycle aircraft propulsion system that in one form includes a gas turbine engine and a ramjet. The gas turbine engine produces an exhaust flow that is offset from an exhaust flow from the ramjet. The two streams can be flowed independent of each other or together depending on the application and relevant portion of a flight envelope. The nozzle includes a movable portion that can selectively open and close an exhaust flowpath for the gas turbine engine. The nozzle includes a surface that provides expansion for both low speed (gas turbine engine) flow and high speed (ramjet) flow. | 05-07-2015 |
Bryan H. Lerg, Carmel, IN US
Patent application number | Description | Published |
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20150128561 | THREE STREAM, VARIABLE AREA, VECTORABLE NOZZLE - An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air. | 05-14-2015 |
Bryan Henry Lerg, Westfield, IN US
Patent application number | Description | Published |
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20120256044 | FLIGHT VEHICLE, PROPULSION SYSTEM AND THRUST VECTORING SYSTEM - One embodiment of the present invention is a unique flight vehicle. Another embodiment is a unique propulsion system. Another embodiment is a unique thrust vectoring system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for flight vehicles, propulsion systems and thrust vectoring systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 10-11-2012 |
20120317957 | AIRCRAFT POWERPLANT - A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat area for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle. | 12-20-2012 |
20120321448 | AIRCRAFT POWERPLANT - A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle. | 12-20-2012 |
Heike Lerg, Hamburg DE
Patent application number | Description | Published |
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20130266621 | STABLE COSMETIC PREPARATION WITH A HIGH PIGMENT CONTENT - A cosmetic preparation comprising ethylhexyl methoxycrylene and at least 20% by weight, based on the total weight of the preparation, of titanium dioxide and/or zinc oxide. | 10-10-2013 |
20150290117 | SENSORILY ATTRACTIVE HYDRODISPERSION COMPRISING WAXES - The invention relates to a hydrodispersion, comprising thickeners, waxes, and oils. The waxes and the overall preparation have specific melting ranges that ensure a pleasant, sensorily light profile and good care effects. | 10-15-2015 |
Michael Kenneth Lerg, Cary, NC US
Patent application number | Description | Published |
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20150348428 | Interactive Detection Training Systems - An interactive detection training system has a testing space with a defined perimeter and testing space coordinates, a virtual hot zone detecting probe, a probe motion tracker positioned in the detecting probe, a virtualization display unit, and a simulation system. | 12-03-2015 |