Combustor with axial staging for a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsJames B. Hoke, Randal G. McKinney, Albert K. Cheung
Life of this patent
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Abstract
A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.
Claims20
A turbofan gas turbine engine combustor, comprising:
- a first fuel injection system that directs a first fuel-air mixture generally along an axis of a combustion chamber, said first fuel injection system operable to supply between ten percent and thirty-five percent of a combustion airflow;
- a second fuel injection system that directs a second fuel-air mixture into said combustion chamber downstream of and in cross-flow arrangement with said first fuel injection system, said second fuel injection system operable to supply between thirty percent and sixty percent of said combustion airflow;
- a multiple of dilution holes in communication with said combustion chamber downstream of said second fuel injection system, said multiple of dilution holes operable to supply between five percent and twenty percent of said combustion airflow;
- an inner liner;
- an outer liner;
- and
- a forward assembly between said inner liner and said outer liner,
- wherein said forward assembly includes a bulkhead liner that defines a bulkhead height, and
- wherein said inner liner and said outer liner are radially spaced between one hundred percent and two hundred percent of said bulkhead height axially proximate to said second fuel injection system.
A turbofan gas turbine engine combustor, comprising:
- a first fuel injection system in communication with a combustion chamber;
- a second fuel injection system that communicates with said combustion chamber downstream of said first fuel injection system to define a forward combustion zone forward of said second fuel injection system and a downstream combustion zone aft of said second fuel injection system, wherein said forward combustion zone defines twenty percent to fifty percent of a total volume of said combustor chamber and said downstream combustion zone defines fifty percent to eighty percent of said total volume of said combustor chamber;
- an inner liner;
- an outer liner;
- and
- a forward assembly between said inner liner and said outer liner,
- wherein said forward assembly includes a bulkhead liner that defines a bulkhead height, and
- wherein said inner liner and said outer liner are radially spaced between one hundred percent and two hundred percent of said bulkhead height axially proximate to said second fuel injection system.
A turbofan gas turbine engine combustor, comprising:
- a first fuel injection system in communication with a combustion chamber;
- and
- a second fuel injection system that communicates with said combustion chamber downstream of said first fuel injection system to define a forward combustion zone forward of said second fuel injection system and a downstream combustion zone aft of said second fuel injection system, wherein said downstream combustion zone forms an axial length of one hundred percent to two hundred and fifty percent of a radial height of said combustion chamber proximate said second fuel injection system;
- an inner liner;
- an outer liner;
- and
- a forward assembly between said inner liner and said outer liner,
- wherein said forward assembly includes a bulkhead liner that defines a bulkhead height, and
- wherein said inner liner and said outer liner are radially spaced between one hundred percent and two hundred percent of said bulkhead height axially proximate to said second fuel injection system.
Dependencies are inferred from the claim text.