Swirling midframe flow for gas turbine engine having advanced transitions
A gas turbine engine can-annular combustion arrangement ( 10 ), including: an axial compressor ( 82 ) operable to rotate in a rotation direction ( 60 ); a diffuser ( 100, 110 ) configured to receive compressed air ( 16 ) from the axial compressor; a plenum ( 22 ) configured to receive the compressed air from the diffuser; a plurality of combustor cans ( 12 ) each having a combustor inlet ( 38 ) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement ( 80 ) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
1. A can-annular gas turbine engine combustion arrangement, comprising:
a rotor shaft rotating in a rotor shaft direction of rotation;
combustor cans each comprising a combustor outlet and a combustor inlet circumferentially offset from the respective combustor outlet in a direction opposite the rotor shaft direction of rotation;
an axial compressor;
a plenum in fluid communication with all combustor inlets and providing fluid communication between the axial compressor and the combustor inlets;
a means for inducing circumferential motion to compressed air in the plenum in the direction opposite the rotor shaft direction of rotation, wherein the means for inducing circumferential motion comprises at least one row of rotating compressor airfoils located upstream from a last row of the rotating compressor airfoils, the at least one row of rotating compressor airfoils configured to impart a counter swirl velocity greater than a velocity of rotation of the rotating airfoils; and
a flow path for conveying the compressed air in the plenum to a respective combustor inlet of a respective combustor can.
2. The can-annular gas turbine engine combustion arrangement of claim 1 , further comprising a curved exit diffuser.
3. The can-annular gas turbine engine combustion arrangement of claim 1 , wherein the means for inducing circumferential motion further comprises a stationary row of guide vanes configured to impart counter swirl to the compressed air exiting the axial compressor.
4. A gas turbine engine can-annular combustion arrangement, comprising:
an axial compressor operable to rotate in a rotation direction;
a diffuser configured to receive compressed air from the axial compressor;
a plenum configured to receive the compressed air from the diffuser;
a plurality of combustor cans each comprising a combustor inlet in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and
an airflow guiding arrangement configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction, the compressed air in the plenum being conveyed through a flow path to a respective combustor inlet of a respective combustor can, wherein the airflow guiding arrangement comprises at least one row of rotating compressor airfoils located upstream from a last row of the rotating compressor airfoils, the at least one row of rotating compressor airfoils configured to impart a counter swirl velocity greater than a velocity of rotation of the rotating airfoils.
5. The gas turbine engine can-annular combustion arrangement of claim 4 , the combustion arrangement further comprising a curved compressor exit diffuser.
6. The gas turbine engine can-annular combustion arrangement of claim 4 , wherein the airflow guiding arrangement further comprises a stationary row of guide vanes configured to impart counter swirl to the compressed air exiting the axial compressor.