EXHAUST TURBINE DIFFUSER (OPTIONS) AND METHOD OF INCREASING THE AREA OUTLET EXHAUST DIFFUSER and minimize flow separation along the portion of the outer wall EXHAUST DIFFUSER

摘要

1. The turbine exhaust diffuser for use with several adjacently last stage blades attached to the turbine rotor, and comprising;an inner circular ring and an outer circular ring, which limit the flow path for the vapor coming from a number of blades of the last stage in a first substantially axial direction at the inlet of the diffuser holes, and rotates substantially 90 ° to the outlet of the diffuser, with the outer cone ring has curved paronapravlyayuschuyu surface extending between the inlet and outlet of the diffuser and having a first portion extending from the inlet of the diffuser holes, and a second portion extending to the outlet diffuser, and said second portion is formed with a deviation from the vertical and passing back towards said inlet diffuser holes creating a secured component stream extending in a second opposite axial direction, and is provided with turbulators.;2. The exhaust diffuser of claim 1 wherein the turbulators are radially spaced annular rows.;3. The exhaust diffuser of claim 2, wherein the baffles in adjacent radially spaced annular rows are aligned in the circumferential direction.;4. The exhaust diffuser of claim 2, wherein the baffles in adjacent radially spaced annular rows are arranged offset in the circumferential direction.;5. The exhaust diffuser of claim 2, wherein said radially spaced annular rows comprise at least two rows.;6. The exhaust diffuser of claim 1 wherein the turbulators are hemispherical projections.;7. The exhaust diffuser of claim 1 wherein the turbulators are hemispherical recess.;8. The exhaust diffuser of claim 1, wherein the baffles have a non-circular shape.;9. The exhaust diffuser of claim 8, wherein the baffles are arranged in radially spaced apart annular rows.;10. The turbine outlet diffuser located adjacent the near final stage blades attached to the turbine rotor, and comprising;an inner circular ring and an outer circular ring, which limit the flow path for the vapor coming from a number of blades of the last stage in a first substantially axial direction at the inlet of the diffuser holes, and rotates substantially 90 ° to the outlet of the diffuser,;wherein the outer diffuser ring has a curved paronapravlyayuschuyu surface extending between the inlet and outlet of the diffuser and having a first portion extending from the inlet of the diffuser holes, and a second portion extending to the outlet of the diffuser outlet, said second portion is formed with a deviation from the vertical and passing back in the direction of said diffuser inlet to create software component stream extending in a second opposite axial direction, and is provided with vortex generators arranged in at least two radially spaced annular rows.;11. The exhaust diffuser of claim 10, wherein the turbulators in the adjacent radially spaced annular rows are arranged offset in the circumferential direction.;12. The exhaust diffuser of claim 10, wherein the baffles are hemispherical recesses.;13. The exhaust diffuser of claim 11, wherein the baffles are hemispherical projections.;14. The exhaust diffuser of claim 10, wherein the turbulators have a non-circular shape.;15. A method of increasing the area of ​​the exhaust outlet of the turbine diffuser and to minimize flow separation along the portion of the outer wall of the turbine exhaust diffuser, comprising;(A) the execution of said portion of the outer wall extending from the inlet of the diffuser holes, oriented in the axial direction to the outlet of the diffuser outlet oriented substantially in a radial direction, with its deviation from the vertical and passing back to the inlet of the diffuser with software thread creation component, extending axially upstream and;(B) performing on said portion of the outer wall turbulence, ensuring the creation of localized turbulence in order to minimize flow separation along said outer wall portion.;16. The method of claim 15, wherein the baffle ring has a radially spaced rows.;17. The method of claim 15, wherein the turbulators have a circular shape.;18. The method of claim 15, wherein the turbulators have a non-circular shape.;19. The method of claim 15, wherein the baffles are projections or recesses.;20. The method of claim 16, wherein the turbulators in the adjacent radially spaced annular rows aligned or offset in a circumferential direction.