초록 ▼

A gas turbine engine is provided. The engine has an axis and a plurality of coaxial turbine discs, including a first disc and a second disc. A face of the first disc is disposed opposite to a face of the second disc. The engine also has a cover plate coaxial with the axis covering the second disc. T

A gas turbine engine is provided. The engine has an axis and a plurality of coaxial turbine discs, including a first disc and a second disc. A face of the first disc is disposed opposite to a face of the second disc. The engine also has a cover plate coaxial with the axis covering the second disc. The second disc includes an arrangement of turbine blade inserts positioned around its periphery. This arrangement is concentric with the plurality of turbine discs. Turbine blade inserts are retained on the second disc at least in part by the cover plate. The engine further comprises a coaxial tie bolt extending through the plurality of coaxial turbine discs, a spanner nut on the end of the tie bold, an arm coaxial with the axis extending from the face of the second disc having a distal end an axial stop extending from the face of the first disc. The distal end is in contact with the axial stop. The axial stop retains the axial movement of the second disc. The cover plate extends axially between the axial stop and the second disc and radially between the arm and the periphery of the second disc.

대표청구항 ▼

1. A gas turbine engine having an axis with a plurality of coaxial turbine discs, said plurality of turbine discs including a first disc and a second disc; wherein a face of the first disc is disposed opposite to a face of the second disc; and a cover plate coaxial with the axis and covering the sec

1. A gas turbine engine having an axis with a plurality of coaxial turbine discs, said plurality of turbine discs including a first disc and a second disc; wherein a face of the first disc is disposed opposite to a face of the second disc; and a cover plate coaxial with the axis and covering the second disc, the second disc further including an arrangement of turbine blade inserts positioned around a periphery of the second disc; the arrangement concentric with the plurality of turbine discs and the turbine blade inserts retained on the second disc at least in part by the cover plate, comprising: a coaxial tie bolt extending through the plurality of coaxial turbine disc;a spanner nut on an end of the tie bolt;an arm coaxial with the axis and extending from the face of the second disc, the arm having a distal endan axial stop extending from the face of the first disc;wherein the distal end is in contact with the axial stop; the axial stop restraining the axial movement of the second disc; and the cover plate extending axially between the axial stop and the second disc and radially between the arm and the periphery of the second disc. 2. The gas turbine engine of claim 1, wherein the spanner nut further comprises a relative rotation restriction features preventing relative rotation with respect to the tie bolt, wherein the features is selected from the group consisting of a dimpled surface, a scalloped surface and a facet and a slot. 3. The gas turbine engine of claim 1, wherein the cover plate comprises a first end and a second end, the first end proximate the axial stop and the second end in contact with a second disc rim face. 4. The gas turbine engine of claim 3, wherein the cover plate comprises a cover plate axial stop extending radially inward from the first end and in physical contact with the axial stop. 5. The gas turbine engine of claim 3, wherein the second disc rim face comprises a plurality of turbine disc pilot tabs on the turbine disc rim face and engaged by the second end of the cover plate. 6. The gas turbine engine of claim 1, wherein the cover plate comprises a resilient material. 7. The gas turbine engine of claim 6, wherein the cover plate is a material selected from the group consisting of nickel, cobalt, Nickel/cobalt alloy and titanium. 8. The gas turbine engine of claim 1, wherein the axial stop is one or more grooves in the first disc. 9. The gas turbine engine of claim 1, wherein the cover plate is a partial face cover plate. 10. The gas turbine engine of claim 1, wherein the axial stop comprises a radial protrusion and axial protrusion, the radial protrusion preventing the axial movement of the second disc and the axial protrusion resisting radial movement of the arm. 11. A turbine assembly comprising: a first turbine disc having a center axis and an radially outer rim and an axial stop;a second turbine disc having an radially outer rim and coaxial with the center axis;an arm coaxial with the center axis and extending axially from the second turbine disc;a turbine cover plate having a first end and a second end and coaxial with the center axis,a tie bolt extending through the first and second turbine disc and coaxial with the center axis;a spanner nut threaded onto an end of the tie bolt;wherein the axial stop is in physical contact with a distal end of the arm and prevents axial movement of the second turbine disc; and the turbine cover plate is clamped between the axial stop and the outer rim, wherein the spanner nut restricts axial movement of the first turbine disc. 12. The turbine assembly of claim 11, wherein the outer rim comprises an arrangement of plural turbine blade inserts, the arrangement coaxial with the second turbine disc, said second end of the cover plate restricting axial movement of the plural turbine blade inserts. 13. The turbine assembly of claim 11, wherein the outer rim comprises a plurality of turbine disc pilot tabs, the pilot tabs in contact with the second end of the cover plate and restricting radial movement of the second end. 14. The turbine assembly of claim 11, wherein the cover plate comprises a cover plate axial stop extending radially inward from the first end and engaging the axial stop of the first turbine disc. 15. The turbine assembly of claim 11, wherein the axial stop is one or more grooves in the first disc. 16. The turbine assembly of claim 11, wherein the second turbine disc is restricted from backward movement. 17. In a gas turbine engine having an axis and first and second turbine disc and a cover plate for the second disc, wherein the first and second discs are coaxial with the axis, the second turbine disc including an arm extending axially from the second turbine disc, the first turbine disc including an axial stop, the second disc also includes a rim around a periphery of the second disc, wherein the cover plate defines at a first and second end concentric openings, each opening with a radius greater than a radius of the arm, a method of retaining the cover plate comprising: arranging the first and second discs over a co-axial tie bolt with the cover plate positioned between the first and second discs;positioning the second end of cover plate proximate the rim of the second disc;positioning the first end proximate an axial stop of the first disc;drawing the first disc axially along the tie bolt into contact with the first end and the arm proximate the axial stop and clamping the cover plate against the axial stop and the rim with a force created by applying a rotation to a spanner nut to thread the spanner nut along the tie bolt; wherein the rotation is coaxial with the axis. 18. The method of claim 17, wherein the rim further comprises a plurality of pilot tabs and the second end is retained against the plurality of pilot tabs. 19. The method of claim 17, wherein the force is predetermined and corresponds to the rotation of the spanner nut.