Abstract: Compounds extracted from Rhodiola rosea have ability to inhibit gelatinases and collagenases activity. The compounds have the chemical structure as shown below.

Abstract: Compounds extracted from Rhodiola rosea have ability to inhibit gelatinases and collagenases activity. The compounds have the chemical structure as shown below.

Abstract: A mixer assembly for use in a combustor of a gas turbine engine, including a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and the main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing. The main mixer further includes a main housing surrounding the pilot housing and defining an annular cavity, a plurality of fuel injection ports for introducing fuel into the cavity, and a swirler arrangement including at least three swirlers positioned upstream from the plurality of fuel injection ports, wherein each swirler of the swirler arrangement has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the fuel injection ports.

Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first compressor positioned downstream of the fan section and in flow communication with at least a portion of the first compressed air flow, wherein the first compressor produces a second compressed air flow having a designated pressure; a combustor positioned downstream of the first compressor and in flow communication with second compressed air flow, wherein the combustor produces combustion products from a mixture of fuel and air; a first turbine positioned downstream of the combustor and in flow communication with combustion products, wherein the first turbine powers the first compressor by means of a first rotatable drive shaft connected therebetween; and, a second turbine positioned downstream of the first turbine and in flow communication with the combustion products exiting the first turbine, wherein the second turbine

Abstract: A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing.

Abstract: A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing.

Abstract: A swirler arrangement for a mixing assembly of a gas turbine engine combustor, where the swirler arrangement has a centerline axis therethrough, including: a swirler housing including an outer radial wall and an upstream wall; a first plurality of vanes incorporated into the outer radial wall, wherein the first plurality of vanes are oriented at a first angle with respect to an axis through the outer radial wall; and, a second plurality of vanes incorporated into the outer radial wall, wherein the second plurality of vanes are oriented at a second angle with respect to the through the outer radial wall. A first type of passage is defined between adjacent first and second vanes having a first configuration and a second type of passage is defined between adjacent first and second vanes having a second configuration so that air flowing through the swirler arrangement is swirled in a desirable manner.

Abstract: A method for operating a gas turbine engine includes coupling an anti-resonant frequency system to a combustor including a premixer assembly and a plurality of damper tubes, and adjusting the anti-resonant frequency system until the anti-resonant frequency of the damper tubes is approximately equal to the combustor resonant frequency.