Delavan Inc.

Siemens Aktiengesellschaft

Rosemount Aerospace Limited

Michael D Cornwell

Jerry Lee Goeke

Vladimir Dusan Milosavljevic

Ephraim J Gutmark

Douglas C Myhre

Randy C Baxter

Nicholas R Overman

Michael John Forst

O Harald Eriksen

Anthony William Newman

A flameless burner for a gas turbine engine includes a burner body having a longitudinal axis, an upstream section and a downstream section. The upstream section of the burner body defines a primary swirl generating chamber having air swirlers associated therewith. The primary swirl generating chamber is adapted and configured to receive compressor discharge air through the air swirlers. The strong swirl of the compressor discharge air forms a recirculation zone that entrains combustion product gases toward the burner body. Fuel injectors are operatively connected to the downstream section of the burner body for issuing fuel into the recirculated combustion product gases.

Flameless combustion systems for gas turbine engines

A system is disclosed for actively controlling combustion in a gas turbine engine, which includes a fuel injector for issuing fuel into a combustion chamber of the gas turbine engine. The fuel injector has a dynamic pressure sensor for measuring acoustic pressure within the combustion chamber and a flame sensor for observing flame characteristics within the combustion chamber. The system further includes a high speed valve assembly for controlling flow of fuel to the injector and an electronic controller associated with the fuel injector for commanding the valve assembly to deliver fuel to the fuel injector at a commanded flow rate, based upon input from the sensors in the fuel injector.

Active combustion control system for gas turbine engines

A valve assembly is disclosed for modulating the flow of fuel to a fuel nozzle at a high frequency or in a stepped manner to actively control combustion in a gas turbine engine which includes a valve housing defining an inlet portion for receiving fuel from a fuel source at an initial flow rate and an outlet portion for delivering fuel to a fuel nozzle at the initial flow rate or a modulated flow rate depending upon a detected combustion condition, and a mechanism disposed within the valve housing for modulating the flow rate of fuel to the outlet portion in response to a detected combustion condition.

Valve assembly for modulating fuel flow to a gas turbine engine

The subject application is directed to burners for gas turbine engines that use a pilot flame to assist in sustaining and stabilizing the combustion process. An embodiment of the disclosed burners includes, inter alia, a burner housing, a pilot combustor and a quencher. The burner housing has axially opposed upstream and downstream end portions. Additionally, the housing has at least one main fuel inlet passage and at least one main air inlet passage which are adapted to supply fuel and air respectively to an internal chamber defined in the housing. The pilot combustor is disposed along the axis of the burner housing and has an inlet for receiving a rich fuel and air mixture, a combustion chamber within which the rich fuel and air mixture is combusted into combustion products, and an outlet for exhausting the combustion products from the combustion chamber. The quencher is disposed within the internal chamber of the burner housing along the central axis and positioned at the outlet of the pilot combustor. The quencher has an air inlet and a plurality of radially-oriented air outlets for directing cooling air toward the outlet of the pilot combustor and quenching the combustion products exhausted from the pilot combustor.

Pilot combustor for stabilizing combustion in gas turbine engines

An airblast fuel injector assembly for use in conjunction with a gas turbine is disclosed which includes an elongated tubular body having first and second concentric tubes separated from one another by a helical spacer wire so as to define a fuel passage therebetween. The injector assembly is situated such that fuel flow exiting the fuel passage is intersected by an air flow at a predetermined angle of incidence so as to atomize the fuel flow.

Growing community of inventors

Bloomington, MN, United States of America

Michael D Cornwell