Aspects of the invention relate to a compressor system for a turbine engine that not only provides large compressor seal clearances as the engine passes through non-standard operating conditions, but also minimizes the clearances during normal engine operation, thereby increasing the efficiency of t
Aspects of the invention relate to a compressor system for a turbine engine that not only provides large compressor seal clearances as the engine passes through non-standard operating conditions, but also minimizes the clearances during normal engine operation, thereby increasing the efficiency of the compressor. In one embodiment, a substantially annular seal land is secured at one end to an annular extension arm on a compressor disk. When the engine reaches steady state operation, the non-attached end of the seal land can extend radially outward to reduce the clearance between the seal land and a shroud extending over the ends of the adjacent stationary airfoils. The seal land can be designed to resist the rotational forces imparted by the turning rotor until a certain desired operating condition is reached. In one embodiment, the seal land reaches full extension when the engine is operating at about 3600 rpm.
대표청구항▼
What is claimed is: 1. A compressor system for a turbine engine comprising: a disk secured to a rotor, the disk having a leading axial face and a trailing axial face, wherein at least one of the leading face and the trailing face includes an arm projecting axially therefrom and extending annularly
What is claimed is: 1. A compressor system for a turbine engine comprising: a disk secured to a rotor, the disk having a leading axial face and a trailing axial face, wherein at least one of the leading face and the trailing face includes an arm projecting axially therefrom and extending annularly about the respective face; and at least one substantially annular seal land having first and second axial ends, wherein at least the first end of the seal land is disposed over the arm and at least a portion of the first end of the seal land is fixed to the arm, wherein the second end of the land is movable between a first position, in which the majority of the seal land is substantially adjacent to the seal arm, and a second position, in which at least the second end of the seal land moves radially outward in response to rotational forces created by the turning of the rotor. 2. The system of claim 1 wherein the seal land is biased toward the first position. 3. The system of claim 1 wherein the arm includes a proximal region and a distal region, the first end of the seal arm is fixed in the proximal region of the arm. 4. The system of claim 1 wherein the first end of the seal land is fixed to the arm by one of fasteners, brazing and welding. 5. The system of claim 1 wherein the second end of the seal land is flared radially outward. 6. The system of claim 5 wherein at least a portion of the flared second end of the seal land extends axially beyond the arm. 7. The system of claim 1 wherein the seal land has a distribution of mass along the axial length of the seal land, wherein the distribution of mass is concentrated at the second end. 8. The system of claim 1 wherein the seal land has an associated spring rate, the spring rate being such that the second end of the seal land begins to move from the first position when the rotor is rotating at about 3000 rpm. 9. The system of claim 1 wherein the seal land has an associated spring rate, the spring rate being such that the second end of the seal land is substantially in the second position when the rotor is rotating at about 3600 rpm. 10. A compressor system for a turbine engine comprising: a first disk secured to a rotor, the first disk having a leading axial face and a trailing axial face, wherein at least the trailing face includes an arm projecting axially therefrom and extending annularly about the trailing face; a second disk secured to the rotor downstream of the first disk, the second disk having a leading axial face and a trailing axial face, wherein at least the leading face includes an arm projecting axially therefrom and extending annularly about the leading face; a substantially annular seal land for each of the arms, each seal land having first and second axial ends, wherein at least the first end of each seal land is disposed over the arm and at least a portion of the first end of the seal land is fixed to the arm; a plurality of stationary vanes extending radially inward toward the rotor and disposed between the first and second disks, a shroud extending over the ends of each of the plurality of vanes, the shroud being near at least the second end of the seal lands, wherein the second end of the seal lands are movable between a first position defining an initial gap between the second end of the seal lands and the shroud and a second position in which at least the second end of the seal lands move radially outward in response to rotational forces of the turning rotor so as to reduce the gap. 11. The system of claim 10 wherein the seal land is biased toward the first position. 12. The system of claim 10 wherein the second end of each seal land is flared radially outward. 13. The system of claim 10 further including one or more seals strips are attached to the shroud and extend radially away therefrom, wherein the gap is defined between the second end of the seal lands and the ends of the seal strips. 14. The system of claim 10 wherein the seal land has an associated spring rate, the spring rate being such that the second end of the seal land begins to move from the first position when the rotor is rotating at about 3000 rpm. 15. The system of claim 10 wherein the seal land has an associated spring rate, the spring rate being such that the second end of the seal land is substantially in the second position when the rotor is rotating at about 3600 rpm. 16. The system of claim 10 wherein the arm includes a proximal region and a distal region, the first end of the seal land is fixed in the proximal region of the arm. 17. The system of claim 10 wherein the first end of the seal land is fixed to the arm by one of fasteners, brazing and welding. 18. The system of claim 10 wherein the seal land has a distribution of mass along the axial length of the seal land, wherein the distribution of mass is concentrated at the second end. 19. A method for increasing the efficiency of a turbine engine compressor comprising the steps of: (a) providing a turbine engine having a compressor section, the compressor section including: a first disk secured to a rotor; a second disk secured to the rotor downstream of the first disk, each of the disks having a leading axial face and a trailing axial face, wherein at least one of the trailing face of the first disk and the leading face of the second disk includes an arm projecting axially therefrom and extending annularly about the face; a substantially annular seal land having first and second axial ends, wherein at least the first end of the seal land is disposed over the arm and at least a portion of the first end of the seal land is fixed to the arm; a row of radially inwardly extending stationary vanes, the vanes disposed adjacently downstream of the first disk, each of the plurality of vanes terminating at a vane shroud near the seal lands, wherein an initial gap is defined between the second end of the seal lands and the vane shroud; (b) operating the turbine engine such that the compressor rotor turns at about 2300 rpms to about 3600 rpms; and (c) using the rotational forces of the turning rotor to move at least the second end of the seal land radially outward from the first position so as to reduce but not completely close the gap. 20. The method of claim 19 wherein the second end of the seal land is fully radially outwardly extended at about 3600 rpms.
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이 특허에 인용된 특허 (7)
Gardner James F. (Exeter RI), Compliant finer seal.
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