초록 ▼

An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally ra

An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.

대표청구항 ▼

1. An airfoil in a gas turbine engine comprising: an outer wall comprising a leading edge portion including a leading edge, a trailing edge portion including a trailing edge, a pressure side, a suction side, a radially inner end, and a radially outer end, wherein a chordal direction is defined betwe

1. An airfoil in a gas turbine engine comprising: an outer wall comprising a leading edge portion including a leading edge, a trailing edge portion including a trailing edge, a pressure side, a suction side, a radially inner end, and a radially outer end, wherein a chordal direction is defined between the leading and trailing edges and a radial direction is defined between the radially inner and outer ends;a cooling fluid cavity defined in the outer wall, the cooling fluid cavity receiving cooling fluid for cooling the outer wall; anda cooling system that receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall, the cooling system comprising: a plurality of radially spaced-apart first impingement channels extending generally in the chordal direction from the cooling fluid cavity to a first cooling fluid chamber for delivering cooling fluid from the cooling fluid cavity to the first cooling fluid chamber;a plurality of radially spaced-apart second impingement channels extending generally in the chordal direction from the first cooling fluid chamber to a second cooling fluid chamber for delivering cooling fluid from the first cooling fluid chamber to the second cooling fluid chamber; anda plurality of radially spaced-apart third impingement channels extending generally in the chordal direction from the second cooling fluid chamber to a third cooling fluid chamber for delivering cooling fluid from the second cooling fluid chamber to the third cooling fluid chamber, the third cooling fluid chamber being defined by opposing first and second sidewalls comprising respective alternating angled sections that provide the third cooling fluid chamber with a zigzag shape and comprising a plurality of turbulating features provided within the third cooling fluid chamber, the turbulating features effecting a turbulated flow of cooling fluid through the third cooling fluid chamber and being formed in the first and second sidewalls such that a chordal spacing between adjacent turbulating features is substantially equal to or less than a chordal width of the turbulating features. 2. The airfoil according to claim 1, wherein the first, second, and third cooling fluid chambers each have a direction of elongation in the radial direction. 3. The airfoil according to claim 1, further comprising a plurality of outlet passages extending from the third cooling fluid chamber to the trailing edge of the outer wall, the outlet passages receiving cooling fluid from the third cooling fluid chamber and discharging the cooling fluid from the airfoil. 4. The airfoil according to claim 1, wherein the alternating angled sections of the first and second sidewalls that define the third cooling fluid chamber comprise at least a first section angled toward one of the pressure side and the suction side of the outer wall in a downstream direction and at least a second section extending from the first section and angled toward the other of the pressure side and the suction side of the outer wall in the downstream direction. 5. The airfoil according to claim 4, wherein the angles of the second sections are substantially equal and opposite to the angles of the first sections and the first and second sidewalls are continuously curved. 6. The airfoil according to claim 5, wherein the angles of the first sections are within a range of about (15) to about (60) degrees relative to the chordal direction, and the angles of the second sections are with a range about (−15) to about (−60) degrees relative to the chordal direction. 7. The airfoil according to claim 4, wherein opposed angled sections of the respective first and second sidewalls are generally parallel to one another and define inflection points at apices thereof. 8. The airfoil according to claim 1, wherein the cooling fluid cavity extends generally radially between the inner and outer ends of the outer wall. 9. The airfoil according to claim 1, wherein the first and second impingement channels are radially offset with respect to one another. 10. The airfoil according to claim 9, wherein the second and third impingement channels are radially offset with respect to one another. 11. The airfoil according to claim 10, wherein the first impingement channels are generally radially aligned with the third impingement channels. 12. The airfoil according to claim 1, wherein the first and second sidewalls that define the third cooling fluid chamber have outer surfaces that define respective portions of the pressure and suction sides of the outer wall. 13. The airfoil according to claim 1, wherein a dimension of the third cooling fluid chamber in the circumferential direction is greater than a dimension of the radially spaced-apart third impingement channels in the circumferential direction. 14. An airfoil assembly in a gas turbine engine comprising: a platform assembly; andan airfoil comprising: an outer wall coupled to the platform assembly and comprising a leading edge portion including a leading edge, a trailing edge portion including a trailing edge, a pressure side, a suction side, a radially inner end, and a radially outer end, wherein a chordal direction is defined between the leading and trailing edges and a radial direction is defined between the radially inner and outer ends;a cooling fluid cavity defined in the outer wall, the cooling fluid cavity receiving cooling fluid from the platform assembly for cooling the outer wall; anda cooling system that receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall, the cooling system comprising: a plurality of radially spaced-apart first impingement channels extending generally in the chordal direction from the cooling fluid cavity to a first cooling fluid chamber for delivering cooling fluid from the cooling fluid cavity to the first cooling fluid chamber, the first cooling fluid chamber having a direction of elongation in the radial direction;a plurality of radially spaced-apart second impingement channels extending generally in the chordal direction from the first cooling fluid chamber to a second cooling fluid chamber for delivering cooling fluid from the first cooling fluid chamber to the second cooling fluid chamber, the second cooling fluid chamber having a direction of elongation in the radial direction;a plurality of radially spaced-apart third impingement channels extending generally in the chordal direction from the second cooling fluid chamber to a third cooling fluid chamber for delivering cooling fluid from the second cooling fluid chamber to the third cooling fluid chamber, the third cooling fluid chamber having a direction of elongation in the radial direction and being defined by opposing first and second sidewalls comprising respective alternating angled sections that provide the third cooling fluid chamber with a zigzag shape when viewed from a radially outer side of the cooling system;a plurality of outlet passages extending from the third cooling fluid chamber to the trailing edge of the outer wall, the outlet passages receiving cooling fluid from the third cooling fluid chamber and discharging the cooling fluid from the airfoil; and a plurality of turbulating features provided within the third cooling fluid chamber, the turbulating features effecting a turbulated flow of cooling fluid through the third cooling fluid chamber, wherein the turbulating features are formed in the first and second sidewalls such that a chordal spacing between adjacent turbulating features is substantially equal to or less than a chordal width of the turbulating features. 15. The airfoil assembly according to claim 14, wherein: the alternating angled sections of the sidewalls that define the third cooling fluid chamber comprise at least a first section angled toward one of the pressure side and the suction side of the outer wall in a downstream direction and at least a second section extending from the first section and angled toward the other of the pressure side and the suction side of the outer wall in the downstream direction; andthe opposing angled sections of the respective first and second sidewalls are generally parallel to one another and define inflection points at apices thereof. 16. The airfoil assembly according to claim 15, wherein: the angles of the second sections are substantially equal and opposite to the angles of the first sections; andturns between adjacent sections of each of the first and second sidewalls comprise continuously curved walls. 17. The airfoil assembly according to claim 14, wherein: the first and second impingement channels are radially offset with respect to one another; andthe second and third impingement channels are radially offset with respect to one another. 18. The airfoil assembly according to claim 14, wherein the first and second sidewalls that define the third cooling fluid chamber have outer surfaces that define respective portions of the pressure and suction sides of the outer wall.