SWIRL CAN PRIMARY COMBUSTOR

• US 3,748,853 A
• Filed: 10/27/1971
• Issued: 07/31/1973
• Est. Priority Date: 10/27/1971
• Status: Expired due to Term

• Current Assignee: Richard W. Niedzwiecki, Robert E. Jones
• Original Assignee: Richard W. Niedzwiecki, Robert E. Jones
• Inventors: Jones, Robert E., Niedzwiecki, Richard W.
• Primary Examiner(s): Gordon, Clarence R.
• Application Number:
  US05/192,970
• Time in Patent Office: 643 Days
• Field of Search: 60/39.65,39.23,39.29,39.72,39.74R 431/9,173
• US Class Current: 60/737
• CPC Class Codes: F23R 3/14 by using swirl vanes
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A swirl can full annulus combustor operable over a wide range of exit average temperatures is used in a high performance gas turbine engine for advanced aircraft. A large number of swirl can modules are mounted in an array in each combustor.

Claims

1. A combustor for a high performance gas turbine engine comprising a pair of spaced walls forming a full annulus, a duct for supplying compressed air to an annular space between said spaced walls, a plurality of spaced modules mounted in said annular space adjacent to said duct whereby said compressed air is directed toward said modules so that a first portion of said compressed air passes through said modules and a second portion passes around said modules in the space therebetween, each of said modules comprising a hollow cylindrical housing having an open end for receiving said first portion of said compressed air forming primary combustion air, means for injecting fuel tangentially into said housing to provide a mixture of air and fuel, and a plurality of vanes at one end of said housing opposite said open end for swirling said mixture of air and fuel prior to mixing with secondary air, said secondary air comprising said second portion of said compressed air that flows around said modules, said first and said second portions comprising substantially the entire amount of said compressed air supplied from said duct, a film cooled liner on the oposite side of said modules from said duct forming a combustion chamber for receiving said mixture of air and fuel and said secondary combustion air, and means for igniting said mixture of air and fuel in said combustion chamber.

2. A combustor as claimed in claim 1 including means for separately controlling the flow of fuel to certain of said modules whereby said modules are selectively ignited thereby enabling said engine to be operated at off design conditions.

3. A combustor as claimed in claim 1 including means for stabilizing combustion flame adjacent said vanes.

4. A combustor as claimed in cLaim 3 wherein the means for stabilizing combustion flame comprises a substantially flat plate extending outward from said vanes.