| Patent application number | Description | Published |
|---|
| 20080286107 | Course of leading edges for turbomachine components - The course of the leading edges of turbomachine components, such as rotor blades and stator vanes is defined mathematically exactly and repeatedly as well as aerodynamically advantageously by the respective axial coordinate in the direction of the machine axis in relation to the blade height in percent, extending from the blade tip as per equation (1): | 11-20-2008 |
| 20090044543 | Jet engine with compressor air circulation and method for operating the jet engine - In a jet engine with compressor air circulation provided for stabilizing the flow conditions, the compressed hot compressor air tapped from the flow path of the compressor ( | 02-19-2009 |
| 20090208324 | Casing structure for stabilizing flow in a fluid-flow machine | 08-20-2009 |
| 20090238677 | Centrifugal compressor with air extraction and return at the casing - A centrifugal compressor includes a rotor | 09-24-2009 |
| 20090238682 | Compressor stator with partial shroud - A gas-turbine axial compressor has a casing | 09-24-2009 |
| 20090301102 | Gas-turbine compressor with bleed-air tapping - A gas-turbine compressor has a casing | 12-10-2009 |
| 20100021310 | METHOD FOR IMPROVING THE FLOW CONDITIONS ON THE PROPELLER OR FAN OF AN AIRCRAFT ENGINE AND ACCORDINGLY DESIGNED HUB CONE - At a propeller ( | 01-28-2010 |
| 20100098530 | COMPRESSOR FOR A GAS TURBINE - A compressor for a gas turbine, in particular an aircraft gas turbine, has a rotor hub carrying rotor blades, a stator equipped with stator vanes, a shroud associated to the stator vanes, and an arrangement providing sealing between the shroud and rotor hub to prevent leakage. To achieve almost complete suppression of leakage air and, concurrently, simplification of design and manufacture, the sealing arrangement ( | 04-22-2010 |
| 20100111702 | HUB CONE FOR AN AIRCRAFT ENGINE - A hub cone ( | 05-06-2010 |
| 20100139278 | METHOD AND APPARATUS FOR THE OPERATION OF A TURBOPROP AIRCRAFT ENGINE PROVIDED WITH PUSHER PROPELLERS - A method and an apparatus is disclosed for the operation of a turboprop aircraft engine provided with pusher propellers. In order to reduce thermal loading of the pusher propellers impaired by the hot exhaust-gas flow of the engine and increase the service life of the pusher propellers, cold air from the environment outside of the aircraft engine is fed into, and mixed with, the hot exhaust-gas flow passing the pusher propellers and their connecting structure before the hot exhaust-gas flow reaches the pusher propellers. | 06-10-2010 |
| 20100232954 | BYPASS DUCT OF A TURBOFAN ENGINE - In the area of the support struts and/or the aerodynamic fairings downstream of the stator vanes, the cross-section of the bypass duct of a turbofan engine is enlarged such that the pressure variations caused by the stagnation effect of the installations and reacting on the fan are reduced, enabling the fan to be operated with more efficiency and stability and finally the losses of the overall system and the fuel consumption to be reduced. The cross-sectional enlargement is accomplished by modifying the course of the wall in a limited area, actually by gradually enlarging the flow cross-section in the bypass duct in the axial and in the circumferential direction, with this enlargement being confined to the area around the leading edge of the support struts and/or the aerodynamic fairings. | 09-16-2010 |
| 20110011058 | TURBOFAN ENGINE - With a turbofan engine the inner sidewall ( | 01-20-2011 |
| 20110014037 | Axial-flow compressor with a flow pulse generator - Axial-flow compressor including, within a compressor casing ( | 01-20-2011 |
| 20110014058 | PROPELLER - On a propeller, more particularly one for aircraft applications, an efflux slot ( | 01-20-2011 |
| 20110016883 | Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine - The aerodynamically shaped, symmetrical cross-sectional profile for the struts or the fairing ( | 01-27-2011 |
| 20110027091 | Axial-flow compressor, more particularly one for an aircraft gas-turbine engine - On an axial-flow compressor, more particularly one for an aircraft gas-turbine engine, including at least one rotor disposed in a casing and having compressor blades extending from a rotor hub as well as one stator, a slot-type recess ( | 02-03-2011 |
