Rolls-royce Deutschland Ltd & Co. Kg

Rolls-royce Corporation

Imon-Kalyan Bagchi

Luca Tentorio

Juan Carlos Roman Casado

Jonathan Knapton

Filippo Zambon

Waldemar Lazik

Radu Irimia

Giacomo Di Chiaro

James Robins

Thomas Doerr

Leif Rackwitz

Tomasz Stankowski

A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the lean burn fuel injector head tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction for a length and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, wherein the combustor chamber includes primary and secondary combustion zones. A ratio of the combustor chamber length to the lean burn fuel injector head tip diameter is less than 5.

Combustor with improved aerodynamics

A lean burn combustor includes a plurality of lean burn fuel injectors, each including a fuel feed arm and a lean burn fuel injector head with a lean burn fuel injector head tip, wherein the tip has a lean burn fuel injector head tip diameter, the lean burn fuel injector head including a pilot fuel injector and a main fuel injector, the main fuel injector being arranged coaxially and radially outwards of the pilot fuel injector; and a combustor chamber extending along an axial direction and including a radially inner annular wall, a radially outer annular wall, and a meter panel defining the size and shape of the combustor chamber, which includes a primary combustion zone with a primary combustion zone depth and a secondary combustion zone. A ratio of the primary combustion zone depth to the lean burn fuel injector head tip diameter is less than 2.4.

Lean burn combustor

A fuel injector including: a plurality of air swirler passages; at least one fuel supply passage arranged to supply fuel into at least one of the air swirler passages; and at least one cavity separating an exterior of the fuel supply passage from a body of the fuel injector; wherein the cavity is at least partially filled with a thermally insulating material.

Fuel injector

A fuel spray nozzle including a primary atomizer to discharge a flow of swirled atomised fuel along and around a fuel spray nozzle axis. The primary atomiser includes outer air swirler disposed radially outwardly of a fuel pre-filmer channel. A secondary atomiser disposed around the primary atomiser includes secondary inner air swirler to swirl flow along an inner air channel. The secondary inner air swirler disposed radially inwardly of a secondary fuel pre-filmer channel of the secondary atomiser. A primary outer air channel defined between the primary outer swirler and the secondary inner swirler. The secondary inner air swirler include splitter wall to separate swirling flow in the secondary inner channel from the primary flow of atomised fuel. The secondary inner air swirler includes primary cap wall integral with and extending radially inwardly from the splitter wall to direct flow from the primary outer channel inwardly towards the fuel spray.

Fuel spray nozzle for gas turbine engine

This invention relates to a lean premix burner of a gas-turbine engine with an annular central body, which, while being essentially concentric to a burner center axis, is provided with an annular ductconnected to a supply lineand with a film applicatorwhich conically widens at the fuel exit side and into whose radially inward area at least one fuel exit openingissues which is connected to the annular duct, characterized in that the film applicatorhas, adjacently to and downstream of the fuel exit openingsin the area facing the fuel exit side, a step-like, annular protruding areadisposed radially to the burner center axis.

Lean premix burner of a gas-turbine engine provided with a concentric annular central body

This invention relates to a lean premix burner of a gas-turbine engine with an annular central body, which, while being essentially concentric to a burner center axis, is connected to a film applicator, which conically widens at the fuel exit side, as well as to an outer ringconcentrically arranged to the burner center axisand surrounding at least the film applicatorat a certain distance, characterized in that an annular flow-guiding elementis provided in an annular ductformed between the outer ringand the film applicatorwhich, in the axial direction of the annular duct, is at least partly situated outside of the outer ring

Lean premix burner of a gas-turbine engine provided with a flow-guiding element

A gas-turbine lean combustor includes a combustion chamber () and a fuel nozzle () which includes a pilot fuel injection () and a main fuel injection (). The main fuel injection () includes central recesses () for a controlled inhomogeneous fuel injection, the number of said recesses on the circumference ranging from 8 to 40 and said recesses having an angle of inclination &#x3b4;in circumferential direction of 10&#xb0;&#x2266;&#x3b4;&#x2266;60&#xb0; and an axial angle of inclination &#x3b4;relative to the combustor axis () between &#x2212;10&#xb0;&#x2266;&#x3b4;&#x2266;90&#xb0;.

Growing community of inventors

Berlin, Germany

Imon-Kalyan Bagchi