High inlet mach combustor for gas turbine engine

A combustor for a gas turbine engine having a compressor providing compressed air flow, comprising:

• (a) an outer liner;
• (b) an inner liner spaced from said outer liner, wherein a combustion chamber is defined therebetween;
• (c) a dome inlet module in flow communication with said compressed air flow having an outer member fixed to said outer liner and an inner member fixed to said inner liner, wherein a flow passage is defined therebetween for an air stream to flow from said compressor to said combustion chamber, said dome inlet module further comprising a plurality of vanes positioned circumferentially within said flow passage;
• and
• (d) means for injecting fuel into said flow passage, wherein said fuel mixes with said air stream to form a fuel/air mixture which enters said combustion chamber;
• wherein said vanes have a blunt trailing edge to generate wakes and shear layers within said flow passage, whereby mixing of said fuel with said air stream is enhanced.

A combustor for a gas turbine engine having a compressor providing compressed air flow, comprising

• (a) an outer liner;
• (b) an inner liner spaced from said outer liner, wherein a combustion chamber is defined therebetween;
• (c) a dome inlet module in flow communication with said compressed air flow having an outer member fixed to said outer liner and an inner member fixed to said inner liner, wherein a flow passage is defined therebetween for an air stream to flow from said compressor to said combustion chamber;
• (d) means for injecting fuel into said flow passage, wherein said fuel mixes with said air stream to form a fuel/air mixture which enters said combustion chamber;
• (e) a casing around said combustor, wherein an outer passage is formed between said casing and said outer liner and an inner passage is formed between said casing and said inner liner;
• (f) a heat exchanger positioned adjacent said casing;
• (g) a bleed opening adjacent said dome inlet module for diverting a portion of said compressed air;
• (h) an entry duct for channeling said portion of said compressed air into said heat exchanger;
• (i) a fuel passage to said heat exchanger, wherein said fuel entering said heat exchanger cools said compressed air entering said heat exchanger;
• and
• (j) an exit duct for channeling said cooled compressed air into said outer passage and a hollow turbine nozzle positioned immediately downstream of said combustion chamber, wherein a portion of said cooled compressed air enters said outer passage and a portion of said cooled compressed air flows through said turbine nozzle and into said inner passage.