Olmes
James Brewster Olmes, Agoura Hills, CA US
Patent application number | Description | Published |
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20090086582 | Dual Illumination Watch Face, And Associated Methods - Systems and methods for a dual illumination watch face having a tritium gas tube coupled with a dial, minute hand or hour hand of the watch face, and phosphorescent material disposed with at least one of the dial, minute hand and hour hand. | 04-02-2009 |
20110158056 | Dual Illumination Watch Face, And Associated Methods - Systems and methods for a dual illumination watch face having a tritium gas tube coupled with a dial, minute hand or hour hand of the watch face, and phosphorescent material disposed with at least one of the dial, minute hand and hour hand. | 06-30-2011 |
Sven Olmes, Villigen CH
Patent application number | Description | Published |
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20080247867 | GAP SEAL IN BLADES OF A TURBOMACHINE - A gap seal ( | 10-09-2008 |
20090067984 | GAS TURBINE WITH AXIAL THRUST BALANCE - A method for axial thrust control of a gas turbine, and a gas turbine with a device for controlling axial thrust are provided. A gas turbine, with regard to aerodynamic forces and pressure forces, which exert an axial force upon the rotor, is configured such that at no-load and low partial load it has a negative thrust, and at high load it has a positive thrust. In order to ensure a resulting positive thrust upon the thrust bearing within the entire load range of the gas turbine, an additional thrust is applied in a controlled manner. The additional thrust for example can be controlled in dependence upon the gas turbine load. The resulting thrust force at full load is consequently less than in the case of a conventionally designed gas turbine without thrust balance. | 03-12-2009 |
20090243221 | LEAF SEAL FOR A TURBOMACHINE - A leaf seal is provided for sealing a radial gap between a stator and rotor of a turbo machine. The seal includes a plurality of metallic sealing leaves, arranged in a row and attached to a carrier. The leaves are arranged concentrically around the circumference of the rotor and are arranged inclined at an angle to the radial direction of the rotor and in an opposite direction to the rotation direction and also includes front and rear plates connected to the carrier and extend over a circumference of the seal on both sides of the sealing leaves. A first axial distance is defined between the rear plate and the sealing leaves, and a second axial distance is defined between the front plate and the sealing leaves. An apparatus is also included for actively controlled variation of the first axial distance during operation of the turbomachine. | 10-01-2009 |
Sven Olmes, Windisch CH
Patent application number | Description | Published |
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20120036864 | GAS TURBINE ENGINE AND METHOD FOR COOLING THE COMPRESSOR OF A GAS TURBINE ENGINE - A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine. | 02-16-2012 |
20140086743 | METHOD AND COOLING SYSTEM FOR COOLING BLADES OF AT LEAST ONE BLADE ROW IN A ROTARY FLOW MACHINE - A method and a cooling system for cooling blades of at least one blade row in a rotary flow machine includes an axial flow channel which is radially limited on the inside by a rotor unit and at the outside by at least one stationary component, the blades are arranged at the rotary unit and provide a shrouded blade tip facing radially to said stationary component. Pressurized cooling air is fed through from radially outside towards the tip of each of said blades in the at least one blade row, and the pressurized cooling air enters the blades through at least one opening at the shrouded blades' tip. | 03-27-2014 |
20140112798 | GAS TURBINE AND TURBINE BLADE FOR SUCH A GAS TURBINE - A gas turbine includes a rotor concentrically surrounded by a casing, with an annular hot gas channel axially extending between the rotor and the casing. The rotor is equipped with a plurality of blades, which are arranged on the rotor in an annular fashion. Each of the blades is mounted with a root in a respective axial slot on a rim of the rotor radially extending with an airfoil into said hot gas channel and adjoining with an axially oriented root surface to an annular rim cavity. Cooling means are provided at the root of each of said blades to receive cooling air being injected into said rim cavity through stationary injecting means. An optimized cooling is achieved by providing the root surface to be an essentially plane surface and the cooling means including a scoop for capturing and redirecting at least part of the injected cooling air, which scoop is designed as a recess with respect to the root surface. | 04-24-2014 |