| 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 |
