Patent application number | Description | Published |
20080209911 | Combination engines for aircraft - An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto. | 09-04-2008 |
20080277533 | Aircraft combination engines inlet airflow control system - A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the gas turbine engine having a compressor air transfer duct extending therefrom to an internal combustion engine provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake. | 11-13-2008 |
20080314573 | Aircraft combination engines thermal management system - An engine combination for generating forces with a gas turbine engine generating force that utilizes an engine lubricant for lubricating moving components in the turbofan engine, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force that utilizes a coolant for transporting heat generated in the intermittent combustion engine away therefrom and having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto. A coupling heat exchanger is coupled to both the gas turbine engine and the intermittent combustion engine to have the engine lubricant and the coolant pass therethrough to thereby permit the coolant to transport heat in the engine lubricant away therefrom. A further cooling heat exchanger is coupled to both the coupling heat exchanger and the intermittent combustion engine to have a remote fluid from a source thereof and the coolant pass therethrough to permit the remote fluid to transport heat in the coolant away therefrom, and with the coolant also circulating through at least one of the coupling heat exchanger and the intermittent combustion engine. | 12-25-2008 |
20090047123 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Integrated Back-Up Seals - Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine. | 02-19-2009 |
20090047124 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Anti-Fouling Provisioning - Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner. | 02-19-2009 |
20090051119 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Integrated Back-up Seals - Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a stator assembly and a rotor assembly configured to operatively engage each other to form a first seal and a second seal; the first seal being provided by a hydrostatic seal having a seal face and a seal runner; and the second seal being provided by a back-up seal such that responsive to a failure of the first seal, the back-up seal maintains at least a portion of a pressure differential established by the first seal prior to the failure. | 02-26-2009 |
20090107106 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals - Gas turbine engine systems involving hydrostatic face seals are provided. In this regard, representative compressor assembly for a gas turbine engine includes a compressor having a hydrostatic seal formed by a seal face and a seal runner. | 04-30-2009 |
20090152051 | On-demand lubrication system and method for improved flow management and containment - A method of oil flow management for a gas turbine engine includes moving oil from a tank to a compartment using a pressure pump, moving oil from the compartment to the tank using a scavenge pump, and at least temporarily increasing a rate at which oil is moved with the scavenge pump by a greater amount than a rate at which oil is moved with the pressure pump to create at least a partial vacuum to negatively pressurize the compartment to reduce oil leakage. | 06-18-2009 |
20090212501 | Self-Balancing Face Seals and Gas Turbine Engine Systems Involving Such Seals - Self-balancing face seals and gas turbine engine systems involving such seals are provided. In this regard, a representative self-balancing face seal assembly includes: a rotatable seal runner having a first seal runner face and an opposing second seal runner face; a first face seal operative to form a first seal with the first seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal; and a second face seal operative to form a second seal with the second seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal. | 08-27-2009 |
20110155508 | ON-DEMAND LUBRICATION SYSTEM FOR IMPROVED FLOW MANAGEMENT AND CONTAINMENT - An oil circulation system for a gas turbine engine includes a variable displacement scavenge pump for pumping oil, a first actuator for controlling displacement of the scavenge pump, a variable displacement pressure pump for pumping oil, a second actuator for controlling displacement of the pressure pump, and a drive shaft. Both the scavenge pump and the pressure pump are driven by the drive shaft. | 06-30-2011 |
20110203293 | BEARING COMPARTMENT PRESSURIZATION AND SHAFT VENTILATION SYSTEM - An assembly and method for providing buffer air and/or ventilation air within a gas turbine engine, the assembly includes an accessory gearbox and a centrifugal compressor. The accessory gearbox is connected to a driven shaft of the gas turbine engine. The centrifugal compressor is driven by the accessory gearbox during operation of the gas turbine engine to receive and compress a bleed air to produce the buffer air and/or the ventilation air. The buffer air and/or the ventilation air is communicated within the gas turbine engine. | 08-25-2011 |
20110247344 | REAR HUB COOLING FOR HIGH PRESSURE COMPRESSOR - In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor. | 10-13-2011 |
20120085528 | INTERDEPENDENT LUBRICATION SYSTEMS - A heat exchange system for use in operating equipment having a plurality of subsystems in each of which one of a plurality of working fluids is utilized to provide selected operations with there being an air and working fluid heat exchanger providing controlled cooling to cool at least one of the plurality of working fluids in its corresponding subsystem. In addition, a coupling heat exchanger is also provided connected to two of the subsystems to pass there working fluids therethrough, including the subsystem with the air and working fluid heat exchanger, to allow one of the connected subsystems to aid in cooling the other. | 04-12-2012 |
20120107104 | COMPRESSION SYSTEM FOR TURBOMACHINE HEAT EXCHANGER - An example turbomachine cooling arrangement includes a pump configured to pressurize a first turbomachine fluid that is then communicated through a heat exchanger assembly to remove thermal energy from a second turbomachine fluid. A portion of the pump is configured to be housed within a gearbox housing of a turbomachine. | 05-03-2012 |
20120282079 | REAR HUB COOLING FOR HIGH PRESSURE COMPRESSOR - In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor. | 11-08-2012 |
20130016936 | DUAL MODEL SCAVENGE SCOOP - A system for removing oil from a bearing compartment has a port connected to an end wall of the compartment through which the oil exits the compartment, a scavenge scoop connected to the port for collecting the oil, and a separation device connected to the scavenge scoop for creating an oil collection region. | 01-17-2013 |
20130025290 | INGESTION-TOLERANT LOW LEAKAGE LOW PRESSURE TURBINE - A turbine section of a gas turbine engine includes first and second rotor stages connected by an arm. The first rotor stage has a first set of blades connected to a first rotor disk at a first blade attachment. The second rotor stage has a second set of blades connected to a second rotor disk at a second blade attachment. A cover plate extends from a downstream side of the first blade attachment to an upstream side of the second blade attachment. The cover plate is spaced from the arm so as to define a flow path from the first blade attachment to the second blade attachment. | 01-31-2013 |
20130047623 | ACCESSORY GEARBOX BUFFER COOLING AIR PUMP SYSTEM - A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly. | 02-28-2013 |
20130047624 | DISTRIBUTED LUBRICATION SYSTEM - A gas turbine engine includes a spool, a gearbox having gearing driven by the spool, and a lubrication system. The lubrication system includes a first heat exchanger positioned in a first air flow path, a second heat exchanger positioned in a second air flow path, and a lubrication pump fluidically connected to both the first heat exchanger and the second heat exchanger. A first air fan is driven by the gearbox for inducing air flow through the first air flow path. A second air fan is driven by an electric motor for inducing air flow through the second air flow path. | 02-28-2013 |
20130086922 | Combined Pump System for Engine TMS AOC Reduction and ECS Loss Elimination - A compression pump for an engine is provided. The pump may include a first impeller operatively coupled to a main shaft of the engine, a first inlet configured to at least partially receive bypass airflow, and a first outlet configured to direct compressed air to a thermal management system. | 04-11-2013 |
20130094937 | GAS TURBINE ENGINE OIL BUFFERING - A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment. | 04-18-2013 |
20130097992 | INTEGRATED THERMAL MANAGEMENT SYSTEM AND ENVIRONMENTAL CONTROL SYSTEM FOR A GAS TURBINE ENGINE - A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler. | 04-25-2013 |
20130192239 | GAS TURBINE ENGINE BUFFER SYSTEM - A gas turbine engine includes a buffer system that includes a first circuit and a second circuit. The first circuit can communicate a first buffer supply air to a first portion of the gas turbine engine and the second circuit can communicate a second buffer supply air to a second portion of the gas turbine engine. | 08-01-2013 |
20130192250 | GAS TURBINE ENGINE BUFFER SYSTEM - A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine. The buffer system can include a first circuit and a second circuit. The first circuit selects between a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to render a first buffer supply air having an intermediate pressure. The second circuit selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer supply air. | 08-01-2013 |
20130195627 | THRUST BALANCE SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine has a thrust balance chamber defined between a static housing and a rotating component. The thrust balance chamber is sealed by a first non-contact seal at a radially inner location and a second non-contact seal at a radially outer location. | 08-01-2013 |
20130239582 | CONSTANT SPEED PUMP SYSTEM FOR ENGINE ECS LOSS ELIMINATION - A gas turbine engine has an impeller pump for delivering air to an environmental control system and a speed control pump connected to the impeller pump for driving the impeller pump at a constant speed. | 09-19-2013 |
20130239583 | PUMP SYSTEM FOR HPC EPS PARASITIC LOSS ELIMINATION - An engine includes a duct containing a flow of cool air and a pump system for providing air to an environmental control system. The pump system has an impeller having an inlet for receiving cool air from the duct and an outlet for discharging air to the environmental control system. | 09-19-2013 |
20130239584 | CONSTANT-SPEED PUMP SYSTEM FOR ENGINE THERMAL MANAGEMENT SYSTEM AOC REDUCTION AND ENVIRONMENTAL CONTROL SYSTEM LOSS ELIMINATION - A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed. | 09-19-2013 |
20130239588 | PUMP SYSTEM FOR TMS AOC REDUCTION - An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging air into a discharge manifold. The discharge manifold containing at least one heat exchanger which forms part of a thermal management system. | 09-19-2013 |
20140060075 | GAS TURBINE ENGINE BUFFER SYSTEM - A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a buffer system. The buffer system can include a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit can include a first bleed air supply a second bleed air supply and at least one of an ejector and a valve. The second circuit can include a third bleed air supply, a fourth bleed air supply and at least one of an ejector and a valve. | 03-06-2014 |
20140090355 | REDUCED TRIM FLOW GAS TURBINE ENGINE OIL SYSTEM - A disclosed lubrication system for a gas turbine engine includes a primary passage defining a flow path for lubricant to a gas turbine engine and a bypass passage defining a flow path for lubricant around the gas turbine engine. The lubrication system further includes a primary lubrication pump including a reduced total flow capacity of lubricant with a reduced bypass lubricant flow relative to the total overall flow capacity. | 04-03-2014 |
20140130479 | Gas Turbine Engine With Mount for Low Pressure Turbine Section - A gas turbine engine includes a very high speed low-pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for a higher pressure turbine is at a ratio between about 0.5 and about 1.5. In addition, the lower pressure turbine is mounted with a first bearing mounted in a mid-turbine frame, and a second bearing mounted within a turbine exhaust case. | 05-15-2014 |
20140196470 | GAS TURBINE ENGINE BUFFER SYSTEM - A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure. | 07-17-2014 |
20140318143 | MULTI-CIRCUIT BUFFER SYSTEM FOR A GAS TURBINE ENGINE - A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air. | 10-30-2014 |