About 75 results
https://drivepatents.com/patents/966922 · 26 Nov 2014
In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem (310) defining a fuel path for fuel and a flow guide (3...
https://drivepatents.com/patents/967983 · 29 Oct 2014
A fuel system (10), such as for use in an aircraft, comprises a main pump (14), a servo pump (16), a metering valve (24), a shut-off valve (26), an actuator (20) and a pump sharing valve (12). The main pump (14) and the servo pump (16) receive fuel from a ...
https://drivepatents.com/patents/967975 · 29 Oct 2014
The invention relates to a can-combustor for a can-annular combustor arrangement in a gas turbine, wherein the can combustor (10) at least comprising an essentially cylindrical casing (11) with an axially upstream front panel (13) and an axially downstream...
https://drivepatents.com/patents/969976 · 17 Sep 2014
A fuel system (14) for a gas turbine engine (12) includes an engine fuel manifold (24), a hydraulic actuator (38), and a drain piston assembly (36). The hydraulic actuator (38) actuates in response to a change in pressures within the hydraulic actuator (38...
https://drivepatents.com/patents/972692 · 9 Jul 2014
A valve control device (50) controls the degree of opening of a pressure adjust-ment valve (44), and is provided in a gas turbine (12), which is equipped with: a combustor (22) that generates combustion gas by burning a fuel; a turbine (24) driven by the c...
https://drivepatents.com/patents/973283 · 25 Jun 2014
A fuel routing system 30 of a gas turbine engine 10 includes a primary fuel circuit 32 in communication with a fuel source and a fuel distribution manifold 34. Also included is a secondary fuel circuit 50 extending from the primary fuel circuit 32 to a plu...
https://drivepatents.com/patents/974939 · 14 May 2014
A fuel injector is provided and includes a surface (31) disposed proximate to a flow (32) of a first fluid and a delta wing feature (33). The surface (31) has upstream and downstream portions defined relative to the flow (32) and defines an injector hole (...
https://drivepatents.com/patents/975150 · 7 May 2014
The present invention relates to an axial swirler (43), in particular for premixing of oxidizer and fuel in gas turbines. The swirler comprises (43) a series of swirl vanes (3) with a streamline cross-section, wherein each swirl vane (3) has a leading edge...
https://drivepatents.com/patents/978005 · 26 Feb 2014
The invention relates a method for mixing a dilution air with a hot main flow in a sequential combustion system of a gas turbine (100), wherein the gas turbine essentially comprises at least one compressor, a first combustor which is connected downstream t...
https://drivepatents.com/patents/978769 · 5 Feb 2014
The gas turbine combustion chamber comprises mixing air openings (30), a combustion chamber wall (29) and tiles (31) arranged on the inside of the combustion chamber wall at a certain distance from the combustion chamber. The mixing air openings pass throu...