Combustion apparatus for a gas turbine having separate combustion and vaporization zones

US5473882A · kind A · utility

Assignee

• MTU Motoren-und Turbinen-Union München GmbH · DE

Inventors

• Nikolaos Zarzalis · Dachau, DE
• Thomas Ripplinger · Karlsruhe, DE

Key dates

• Filing date: May 25, 1994
• Grant date: Dec 12, 1995
• Expiry date: May 25, 2014

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A combustion chamber apparatus 1 for a gas turbine has a pilot stage and a main stage for low-emission lean-burn operation. The pilot stage is separate from the main stage and is formed by a flame tube 2 with an upstream first fuel injector 3a and with a secondary combustion zone 7a. The main stage includes a vaporization chamber 4 and a combustion chamber 5, and a second fuel injector 3b is provided at an upstream end of the vaporization chamber 4. The vaporization chamber 4 produces a homogenous fuel-air mixture which will not burn until it is in the combustion chamber 5. In lean-burn operation of the apparatus, the separate arrangement of the two chambers 4, 5 significantly reduces the formation of nitrogen oxides. For use in aircraft gas turbine engines, the apparatus has an annular shape with several main and pilot stages.