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A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one

A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.

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1. A seal assembly for sealing between a rotating component and a stationary component in a turbomachine, the seal assembly comprising: a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at lea

1. A seal assembly for sealing between a rotating component and a stationary component in a turbomachine, the seal assembly comprising: a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough, the axially extending hole extending through the at least one of the plurality of teeth from an upstream, high-pressure side to a downstream, low-pressure side of the at least one tooth and being distanced from a radially innermost surface of the at least one tooth and positioned radially inwardly from a radially innermost surface of an arcuate packing ring,wherein the upstream, high-pressure side is in fluid communication with the downstream, low-pressure side via the at least one axially extending hole. 2. The seal assembly of claim 1, wherein the at least one tooth having an axially extending hole therethrough comprises a first tooth on the upstream, high pressure side. 3. The seal assembly of claim 2, wherein the at least one tooth having an axially extending hole therethrough comprises a first tooth and a second tooth on the upstream, high-pressure side. 4. The seal assembly of claim 1, wherein the plurality of teeth comprise arcuate segments of teeth, the proximal end of the at least one tooth collectively extending continuously about the circumference of the rotating component, and wherein the at least one hole comprises a plurality of circumferentially spaced holes along the arcuate portion of teeth. 5. The seal assembly of claim 1, wherein the at least one hole includes a substantially cylindrical, tubular hole. 6. The seal assembly of claim 1, wherein the at least one hole extends axially through a seal tooth at an axial angle with respect to a centerline of the rotating component and at tangential angle with respect to a circumferential direction of the rotating component, wherein the axial angle is in the range of 0 degrees to 90 degrees and the tangential angle is in the range of 0 degrees to 60 degrees. 7. The seal assembly of claim 1, the seal assembly having a plurality of arcuate portions, each arcuate portion including an arcuate packing ring, wherein each arcuate packing ring is moveably mounted in a circumferential groove in the stationary component. 8. The seal assembly of claim 1, wherein the rotating element is a rotor. 9. A turbomachine comprising: a rotating element;a stationary component substantially surrounding the rotating element; anda seal assembly coupled to the stationary component, the seal assembly including: a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough, the axially extending hole extending through the at least one of the plurality of teeth from an upstream, high pressure side to a downstream, low pressure side of the at least one tooth and being distanced from a radially innermost surface of the at least one tooth and positioned radially inwardly from a radially innermost surface of an arcuate packing ring,wherein the upstream, high-pressure side is in fluid communication with the downstream, low-pressure side via the at least one axially extending hole. 10. The turbomachine of claim 9, wherein the at least one tooth having an axially extending hole therethrough comprises a first tooth on the upstream, high-pressure side. 11. The turbomachine of claim 10, wherein the at least one tooth having an axially extending hole therethrough comprises a first tooth and a second tooth on the upstream, high-pressure side. 12. The turbomachine of claim 9, wherein the plurality of teeth comprise arcuate segments of teeth, the proximal end of the at least one tooth collectively extending continuously about the circumference of the rotating component, and wherein the at least one hole comprises a plurality of circumferentially spaced holes along the arcuate portion of teeth. 13. The turbomachine of claim 9, wherein the at least one hole includes a substantially cylindrical, tubular hole. 14. The turbomachine of claim 9, wherein the at least one hole extends axially through a seal tooth at an axial angle with respect to a centerline of the rotating component and at tangential angle with respect to a circumferential direction of the rotating component, wherein the angle is in the range of 0 degrees to 90 degrees, and the tangential angle is in the range of 0 degrees to 60 degrees. 15. The turbomachine of claim 9, the seal assembly having a plurality of arcuate portions, each arcuate portion including an arcuate packing ring, wherein each arcuate packing ring is moveably mounted in a circumferential groove in the stationary component. 16. The turbomachine of claim 9, wherein the rotating element is a rotor. 17. (The turbomachine of claim 9, wherein the seal assembly is an integral part of the stationary component. 18. The turbomachine of claim 9, wherein the seal assembly is rigidly attached to the stationary component.