Florida Turbine Technologies, Inc.

Mark M Harris

Wesley D Brown

Angel M Garcia

Angel M Garcie

Daniel O Davies

Ross H Peterson

Jeffrey M Crutchfield

Natalie L Marshall

Joseph D Brostmeyer

A test rig that reproduces high temperature and high pressure conditions found in a gas turbine engine for testing materials under these conditions. The test rig includes a combustor surrounded by an upper plenum chamber and an exhaust plenum that receives a hot gas stream from the combustor. A transparent channeling vessel guides the hot gas stream from the combustor over a test specimen on which a material to be tested is mounted. The hot gas stream exits the clear channeling vessel and into the exhaust plenum where the stream is cooled by diluting the stream with cooling air. A viewing portal is located in the exhaust plenum so that the material can be observed through the clear vessel.

Advanced hot section materials and coatings test rig

A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.

Small gas turbine engine with multiple burn zones

A small gas turbine engine where the compressor and turbine are supported on a rotary shaft, and a main bearing is supported on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is used to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.

Gas turbine engine with an air cooled bearing

A small gas turbine engine with a compressor, a combustor, and a turbine located downstream of the combustor. The compressor and turbine are supported on a rotary shaft, and a main bearing is support on the rotary shaft, the main bearing being located in a hot zone of the combustor. The main bearing includes cooling air passages within the races to provide cooling for the bearing. A cooling air is diverted from the compressor and passed through the bearing cooling passages for cooling the bearing, and then the cooling air is directed into the combustor. The cooling air is also passed through a guide nozzle before being passed through the bearing to cool both the guide nozzle and the bearing. A swirl cup injector is sued to deliver the compressed air from the compressor and the cooling air from the bearing into the combustor, the swirl cup injector also acting to draw the cooling air through the bearing.

A small gas turbine engine with a bearing cooling and lubricating passage arrangement for a high speed rotor shaft. The engine includes a bypass fan and a compressor. The rotor shaft includes a central passage extending through the entire shaft, and where the rotor shaft is supported by a forward bearing and a rearward bearing. Cooling air for the bearings is diverted from the bypass air and is channeled through the bearings. Fuel is added to the cooling air at a location upstream of the bearing to provide lubrication. The cooling air and lubricating fuel passes through the bearings and into the rotating central shaft, and is then forced to flow toward a radial passage located adjacent to the combustor. The fuel is collected on the central shaft surface and forced out the radial passage and into the combustor. The cooling air continuous out from the central shaft to be mixed with the engine exhaust.

Small gas turbine engine with lubricated bearings

A rotary cup fuel injector for use in a gas turbine engine, the rotary cup injector being rotatably secured to the rotor shaft and positioned radially inward of the combustor, the rotary cup injector having a front face with a parabolic shape and a rear face with a slanted and flat shape. The front and rear faces of the injector form a thin film of fuel on the surfaces and&#x2014;because of the high rotational speed&#x2014;produce fine droplet's of fuel to be injected into a combustion chamber. The two faces inject fuel into two combustion zones of the combustor.

Growing community of inventors

Palm Beach Gardens, FL, United States of America

Mark M Harris