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A turbine rotor body having at least one inlet orifice in fluid communication with a pre-swirl system such that the inlet orifice receives cooling fluids from the pre-swirl system is disclosed. The inlet orifice may be configured to reduce the relative velocity loss associated with cooling fluids en

A turbine rotor body having at least one inlet orifice in fluid communication with a pre-swirl system such that the inlet orifice receives cooling fluids from the pre-swirl system is disclosed. The inlet orifice may be configured to reduce the relative velocity loss associated with cooling fluids entering the inlet orifice in the rotor, thereby availing the cooling system to the efficiencies inherent in pre-swirling the cooling fluids to a velocity that is greater than a rotational velocity of the turbine rotor body. As such, the system is capable of taking advantage of the additional temperature and work benefits associated with using the pre-swirled cooling fluids having a rotational speed greater than the turbine rotor body.

대표청구항 ▼

1. A turbine rotor, comprising: a turbine rotor body having at least one cooling chamber forming a portion of a cooling system and having a plurality of rows of turbine blades extending radially from the turbine rotor body, wherein the plurality of rows form a plurality of stages of a turbine engine

1. A turbine rotor, comprising: a turbine rotor body having at least one cooling chamber forming a portion of a cooling system and having a plurality of rows of turbine blades extending radially from the turbine rotor body, wherein the plurality of rows form a plurality of stages of a turbine engine;wherein the turbine rotor body is rotationally coupled to at least one stationary component of the turbine engine such that during operation, the turbine rotor body is capable of rotating relative to the at least one stationary component;wherein the cooling system includes at least one pre-swirl system configured to increase the velocity of cooling fluids within the cooling system to a speed that is at least equal to a rotational speed of the turbine rotor body;at least one inlet orifice in fluid communication with the at least one pre-swirl system such that the at least one inlet orifice receives cooling fluids from the pre-swirl system;wherein the at least one inlet orifice includes a diffuser ramp extending generally along an outer surface of the turbine rotor body such that the diffuser ramp extends from an intersection of the outer surface and the turbine rotor body into the turbine rotor body and terminates at the at least one inlet orifice, wherein a volume of the diffuser ramp increases moving from the intersection to the at least one inlet orifice;wherein the diffuser ramp of the at least one inlet orifice has a width greater than a diameter of the inlet orifice;wherein at least a portion of the at least one inlet orifice not formed by the diffuser ramp includes a transition section extending radially therefrom a distance greater than an outer diameter of the inlet orifice but less than an outermost extension of the diffuser ramp;wherein the transition section extends greater than halfway around the inlet orifice; andwherein the diffuser ramp has generally linear sides extending radially from the at least one inlet orifice. 2. The turbine rotor of claim 1, wherein the diffuser ramp of the at least one inlet orifice has a generally linear bottom surface. 3. The turbine rotor of claim 1, wherein the diffuser ramp of the at least one inlet orifice has a generally curved bottom surface extending radially from the at least one inlet orifice. 4. The turbine rotor of claim 1, wherein a channel forming the at least one inlet orifice is generally linear relative to a longitudinal axis of the channel. 5. The turbine rotor of claim 1, wherein a channel forming the at least one inlet orifice is generally curved relative to a longitudinal axis of the channel. 6. The turbine rotor of claim 1, wherein a longitudinal axis of the diffuser ramp is canted relative to a linear axis of the turbine rotor. 7. The turbine rotor of claim 6, wherein the longitudinal axis of the diffuser ramp is aligned with a resultant of a relative velocity vector and an axial velocity vector. 8. The turbine rotor of claim 1, wherein an outlet of the at least one inlet orifice includes an outlet diffuser. 9. The turbine rotor of claim 8, wherein the outlet diffuser is symmetrically wider than a channel forming the at least one inlet orifice in a first direction, and the outlet diffuser is asymmetrically wider than the at least one inlet orifice in a second direction that is generally orthogonal to the first direction, as viewed along an inner surface at the outlet. 10. The turbine rotor of claim 1, wherein the transition section extends about 270 degrees around the inlet orifice. 11. A turbine rotor, comprising: a turbine rotor body having at least one cooling chamber forming a portion of a cooling system and having a plurality of rows of turbine blades extending radially from the turbine rotor body, wherein the plurality of rows form a plurality of stages of a turbine engine;wherein the turbine rotor body is rotationally coupled to at least one stationary component of the turbine engine such that during operation, the turbine rotor body is capable of rotating relative to the at least one stationary component;wherein the cooling system includes at least one pre-swirl system configured to increase the velocity of cooling fluids within the cooling system to a speed that is at least equal to a rotational speed of the turbine rotor body;at least one inlet orifice in fluid communication with the at least one pre-swirl system such that the at least one inlet orifice receives cooling fluids from the pre-swirl system;wherein the at least one inlet orifice includes a diffuser ramp extending generally along an outer surface of the turbine rotor body such that the diffuser ramp extends from an intersection of the outer surface and the turbine rotor body into the turbine rotor body and terminates at the at least one inlet orifice, wherein a volume of the diffuser ramp increases moving from the intersection to the at least one inlet orifice;wherein an outlet of the at least one inlet orifice into the at least one cooling chamber in the turbine rotor body includes an outlet diffuser;wherein at least a portion of the at least one inlet orifice not formed by the diffuser ramp includes a transition section extending radially therefrom a distance greater than an outer diameter of the inlet orifice but less than an outermost extension of the diffuser ramp;wherein a longitudinal axis of the diffuser ramp is canted relative to a linear axis of the turbine rotor;wherein the diffuser ramp of the at least one inlet orifice has a width greater than a diameter of the inlet orifice;wherein the transition section extends greater than halfway around the inlet orifice; andwherein the diffuser ramp has generally linear sides extending radially from the at least one inlet orifice. 12. The turbine rotor of claim 11, wherein the diffuser ramp of the at least one inlet orifice has a generally linear bottom surface. 13. The turbine rotor of claim 11, wherein the diffuser ramp of the at least one inlet orifice has a generally curved bottom surface extending radially from the at least one inlet orifice. 14. The turbine rotor of claim 11, wherein a channel forming the at least one inlet orifice is generally linear relative to a longitudinal axis of the channel. 15. The turbine rotor of claim 11, wherein a channel forming the at least one inlet orifice is generally curved relative to a longitudinal axis of the channel. 16. The turbine rotor of claim 15, wherein the longitudinal axis of the diffuser ramp is aligned with a resultant of a relative velocity vector and an axial velocity vector. 17. The turbine rotor of claim 11, wherein the outlet diffuser is symmetrically wider than a channel forming the at least one inlet orifice in a first direction, and the outlet diffuser is asymmetrically wider than the at least one inlet orifice in a second direction that is generally orthogonal to the first direction, as viewed along an inner surface at the outlet. 18. The turbine rotor of claim 11, wherein the transition section extends about 270 degrees around the inlet orifice. 19. A turbine rotor, comprising: a turbine rotor body having at least one cooling chamber forming a portion of a cooling system and having a plurality of rows of turbine blades extending radially from the turbine rotor body, wherein the plurality of rows form a plurality of stages of a turbine engine;wherein the turbine rotor body is rotationally coupled to at least one stationary component of the turbine engine such that during operation, the turbine rotor body is capable of rotating relative to the at least one stationary component;wherein the cooling system includes at least one pre-swirl system configured to increase the velocity of cooling fluids within the cooling system to a speed that is at least equal to a rotational speed of the turbine rotor body;at least one inlet orifice in fluid communication with the at least one pre-swirl system such that the at least one inlet orifice receives cooling fluids from the pre-swirl system;wherein the at least one inlet orifice includes a diffuser ramp extending generally along an outer surface of the turbine rotor body such that the diffuser ramp extends from an intersection of the outer surface and the turbine rotor body into the turbine rotor body and terminates at the at least one inlet orifice, wherein a volume of the diffuser ramp increases moving from the intersection to the at least one inlet orifice;wherein an outlet of the at least one inlet orifice into the at least one cooling chamber in the turbine rotor body includes an outlet diffuser;wherein at least a portion of the at least one inlet orifice not formed by the diffuser ramp includes a transition section extending radially therefrom a distance greater than an outer diameter of the inlet orifice but less than an outermost extension of the diffuser ramp;wherein a longitudinal axis of the diffuser ramp is canted relative to a linear axis of the turbine rotor such that the longitudinal axis of the diffuser ramp is aligned with a resultant of a relative velocity vector and an axial velocity vector;wherein the diffuser ramp of the at least one inlet orifice has a width greater than a diameter of the inlet orifice;wherein the diffuser ramp of the at least one inlet orifice has a generally linear bottom surface;wherein the outlet diffuser is symmetrically wider than a channel forming the at least one inlet orifice in a first direction, and the outlet diffuser is asymmetrically wider than the at least one inlet orifice in a second direction that is generally orthogonal to the first direction, as viewed along an inner surface at the outlet; andwherein the transition section extends greater than halfway around the inlet orifice.