PRINCIPLES OF NAVAL ENGINEERING 



147.140 



Figure 23-6.— Centrifugal (radial-flow) compressor. 



efficiency, and good flame stability. Additional 

 requirements for the combustion chamber in- 

 clude low rates of carbon formation, light 

 weight, reliability, reasonable length of life, 

 and the ability to mix cold air with the hot com- 

 bustion gases in such a way as to give uniform 

 temperature distribution to the turbine blades. 



Only a small part (perhaps one-fourth) of 

 the air which enters the combustion chamber 

 area is burned with the fuel. The remainder of 

 the air is used to keep the temperature of the 

 combustion gases low enough so that the turbine 

 nozzles and blades will not be overheated and 

 thereby damaged. 



The basic types of combustion chambers in 

 current use are the tubular or can-type chamber, 

 the annular chamber, the can-annular chamber, 

 and the elbow chamber. 



The tubular or can-type chamber, shown in 

 figures 23-7 and 23-8, is used with both axial- 

 flow and centrifugal compressors. The can-type 

 combustion chamber consists of an outer case 

 or housing within which is a perforated, stain- 

 less steel, highly heat resistant combustion 

 chamber liner. The combustion chamber housing 

 is divided to facilitate liner replacement. Each 

 can-type chamber has its own individual air 

 inlet duct. 



Interconnector tubes (flame tubes) are a nec- 

 essary part of can-type combustion chambers. 



-TUMWM VKNES 



rHEAD or LINER 



-SECONDARY AM 



147.141 

 Figure 23-7.— Tubular or can-type combustion 

 chamber. 



600 



