Florida Turbine Technologies, Inc.

Other

Ryznic, John E

Wilson, Jack W., Jr.

Brostmeyer, Joseph D

John E Ryznic

Joseph D Brostmeyer

Jack W Wilson

Wesley D Brown

James Preston Downs

Russell B Jones

Justin T Cejka

George P Liang

John A Orosa

Timothy J Miller

Douglas A Hayes

Brian Potter

William A Spanks, Jr

Brad Carter

Darryl S Eng

Brian A Ryznic

Jr Jack W Wilson

The embodiments provide a system and an apparatus for a combination of a recessed lighting and a smoke detector. A room can include several recessed lights in which one of the recessed lights will include an integral smoke detector that is hidden behind the recessed light. The recess light includes a smoke collecting chamber with several smoke holes to guide any smoke from the room toward the smoke detector. A wall mounted smoke detector testing device can be connected to the smoke detector by a wire in which a person in the room can test the smoke detector without the need to access the smoke detector located above the recessed light.

Combination recessed lighting and smoke detector

A process for retrofitting an industrial gas turbine engine of a power plant where an old industrial engine with a high spool has a new low spool with a low pressure turbine that drives a low pressure compressor using exhaust gas from the high pressure turbine, and where the new low pressure compressor delivers compressed air through a new compressed air line to the high pressure compressor through a new inlet added to the high pressure compressor. The old electric generator is replaced with a new generator having around twice the electrical power production. One or more stages of vanes and blades are removed from the high pressure compressor to optimally match a pressure ratio split. Closed loop cooling of one or more new stages of vanes and blades in the high pressure turbine is added and the spent cooling air is discharged into the combustor.

Process for retrofitting an industrial gas turbine engine for increased power and efficiency

A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.

Apparatus and process of retrofitting a combined cycle power plant

An apparatus and a process for testing a large combustor or a high Mach aero vehicle in a wind tunnel, where liquid air stored in a tank is pumped to a high pressure above 1,500 psi, then vaporized to produce gaseous air at the same high pressure, where the high pressure gaseous air is then heated to a high temperature and then passed into a combustor for testing or passed through a converging diverging nozzle and then into a wind tunnel to produce a non-vitiated gaseous air flow of at least Mach 5 for testing of an aero vehicle. Water can be added to the high pressure liquid air to produce an air flow having a normal water content.

Apparatus and process for testing an aero vehicle at high Mach number

An industrial gas turbine engine in which a compressor includes later stage airfoils that are cooled using a coolant from an external closed loop cooling circuit or from a heat recovery steam generator. Cooling air compressed by a compressor external to the IGT engine can be used for cooling of the main compressor airfoils with a heat exchanger to preheat a fuel used in the combustor. Or, water and steam from a heat recover steam generator can be used to cool the compressor airfoils in which steam can be bled off from the steam generator for cooling and then reintroduced into the HRSG at a downstream stage. Steam is used to cool the rotor blades while water is used to cool the stator vanes.

Multiple staged compressor with last stage airfoil cooling

A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by passing cooling air through the airfoils without discharging film cooling air. The cooling air for the airfoils is bled off from an upstream stage of the compressor, passed through the airfoil to provide for the cooling, passed through a heat exchanger to preheat a fuel, where the preheated fuel is passed into the combustor. the cooled cooling air form the heat exchanger can be reintroduced back into the compressor or passed through the turbine to cool last stage airfoils in the turbine.

A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by passing cooling air through the airfoils without discharging film cooling air. A portion of the compressed air from the discharge of the compressor is bled off and passed through a heat exchanger to preheat a fuel and to cool the compressed air. The cooled compressed air is then passed through the last stage airfoil of the compressor to provide cooling. The cooling air is then reintroduced back into the compressor at an earlier stage or passed through an airfoil in the turbine to provide cooling.

A micro gas turbine engine in which the turbine rotor blades are formed as an integral bladed rotor with cooling air passages formed within the blades and the rotor disk by an EDM process. an adjacent stator vane includes an air riding seal with an air cushion supplied through the vanes to provide cooling, and where the air cushion is then passed into the turbine blades and rotor disk to provide cooling for the turbine blades. With cooling of the turbine blades, higher turbine inlet temperatures for micro gas turbine engines can be produced.

Cooled IBR for a micro-turbine

A turbine rotor blade with a serpentine flow cooling circuit having three legs in which the first leg and the second leg are upward flowing channels each having a series of slanted ribs that define impingement chambers with impingement cooling holes to provide impingement cooling to the airfoil walls. The second leg is a downward flowing leg that contains no metering holes and is substantially unobstructed to the cooling air flow. The rotation of the blade produces a centrifugal force on the airflow passing through the channels with the metering and impingement holes to aid in the flow towards the blade tip. The return channels are unobstructed in order to minimize the pressure loss on the return channel of the serpentine circuit.

Turbine blade with multiple impingement cooled passages

A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by drawing heat away from the airfoils using a heat pipe, and then passing cooling air through a heat exchanger associated with the heat pipe to draw heat away from the heat pipe. The cooling air used for cooling the airfoils is bled off from an earlier stage than the last stage and then discharged into a stage upstream from the bleed off location.

A large floating vertical axis wind turbine with a floating inner cylinder having rotor blades that rotate together as an assembly, and a floating outer cylinder with a central opening in which the floating inner cylinder rotates for support against tipping. Outriggers with floating devices on the ends extend out from the floating outer cylinder for additional stability. The floating inner cylinder is partially supported by a top bearing on the outer cylinder to carry some of the load from the rotor blades.

Floating vertical axis wind turbine

A substrate exposed to high temperatures, the substrate having a TBC layer that includes fibers of reinforcing material to add strength to the layer of TBC. The fibers are made from carbon nanotubes to withstand the high temperatures, and have a diameter of about 0.1 mm or less in order that a thin layer of TBC can completely cover and embed the fibers within the layer. A bond coat is applied to the substrate and the fibers are attached to the bond coat to limit the fibers from being pulled away from the substrate. The carbon nanotubes also provide for improved heat transfer through the TBC to improve the cooling capability of the TBC.

TBC with fibrous reinforcement

A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by passing cooling air through the airfoils without discharging film cooling air. The cooling air for the airfoils is bled off from an upstream stage of the compressor, passed through the airfoil to provide for the cooling, and then discharged back into the compressor at a stage upstream of where the bleed off air was extracted and where the pressure is lower. Because of the high pressure rations, the air temperature in the compressor is at such a high temperature that the last stage airfoils must be cooled to prevent thermal damage.

A turbine rotor blade with a serpentine flow cooling circuit to provide cooling for the airfoil section, where the serpentine flow circuit is formed of a series of up-pass channels and at least one down-pass channel, and where the up-pass channels are formed by a series of impingement cavities separated by slanted ribs each with an impingement hole to direct impingement cooling air against the backside surface of the airfoil wall for cooling, and where the down-pass channel or channels is an open channel to minimize a pressure loss in the cooling air flow. Rotation of the blade produces a centrifugal force on the cooling air flow that increases the pressure of the impingement cooling air at the blade outer radial span wise direction.

Turbine rotor blade

A turbine rotor blade made from the spar and shell construction in which the shell formed from a plurality of shell segments each being a thin wall shell segment made from a high temperature resistant material that is formed by a wire EDM process, and where the shell segments are each secured to the spar separately using a retainer that is poured into retainer occupying spaces formed in the shell segments and the spar, and then hardened to form a rigid retainer to secure each shell segment to the spar individually. The spar includes a number of radial extending projections each with a row of cavities that form the retainer occupying spaces in order to spread the loads around. The retainer can be a bicast material, a transient liquid phase bonding material, or a sintered metal. An old shell can be easily removed and replaced with a new shell by removing parts of the retainer and re-pouring a new retainer with a new shell in place.

Growing community of inventors

Palm Beach Gardens, FL, United States of America

John E Ryznic