Global to push GA events into
skip to main content

Title: Combustor assembly in a gas turbine engine

A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct.
Inventors:
;
Issue Date:
OSTI Identifier:
1082947
Assignee:
Siemens Energy, Inc. (Orlando, FL) NETL
Patent Number(s):
8,375,726
Application Number:
12/431,302
Contract Number:
FC26-05NT42644
Research Org:
Siemens Energy, Inc. (Orlando, FL)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING