GAS TURBINE ENGINE TURBINE DIAPHRAGM WITH ANGLED HOLES
First Claim
1. A gas turbine engine turbine diaphragm, comprising:
- an inner cylindrical portion;
a mounting portion located radially outward from the inner cylindrical portion; and
a disk portion extending radially between the inner cylindrical portion and the mounting portion, the disk portion havinga plurality of angled holes, each angled hole following a vector which is angled in at least one plane with a component of the vector being located on a plane perpendicular to a radial extending from an axis of the diaphragm, the component of the vector being angled relative to an axial direction of the diaphragm.
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Accused Products
Abstract
A gas turbine engine turbine diaphragm (460) includes an inner cylindrical portion (461), a mounting portion (463), and a disk portion (462). The mounting portion (463) is located radially outward from the inner cylindrical portion (461). The disk portion (462) extends radially between the inner cylindrical portion (461) and the mounting portion (463). The disk portion (462) includes a plurality of angled holes (464). Each angled hole (464) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular to a radial extending from an axis of the diaphragm (460). The component of the vector is angled relative to an axial direction of the diaphragm (460).
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Citations
20 Claims
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1. A gas turbine engine turbine diaphragm, comprising:
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an inner cylindrical portion; a mounting portion located radially outward from the inner cylindrical portion; and a disk portion extending radially between the inner cylindrical portion and the mounting portion, the disk portion having a plurality of angled holes, each angled hole following a vector which is angled in at least one plane with a component of the vector being located on a plane perpendicular to a radial extending from an axis of the diaphragm, the component of the vector being angled relative to an axial direction of the diaphragm. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. A gas turbine engine turbine diaphragm, comprising:
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an inner cylindrical portion; a mounting portion located radially outward from the inner cylindrical portion; and a disk portion extending radially between the inner cylindrical portion and the mounting portion, the disk portion having a plurality of angled holes, each angled hole following a vector which is angled in at least one plane with a component of the vector being located on a plane perpendicular to a radial extending from an axis of the diaphragm, the component of the vector being angled from fifty to seventy degrees relative to an axial direction of the diaphragm; and a plurality of first stress relief regions, each stress relief region being contiguous to one of the plurality of angled holes with each first stress relief region having an elongated scoop shape, the elongated scoop shape being wider than a diameter of the contiguous angled hole and biased away from the contiguous angled hole along the component of the vector. - View Dependent Claims (15, 16, 17, 18, 19)
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20. A method for forming angled holes in a turbine diaphragm, the method comprising:
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determining the amount of cooling air needed to cool components aft of the diaphragm; sizing a radius for the angled holes to allow all or a portion of the determined amount of cooling air to pass through the angled holes; selecting an angle for the angled holes; sizing a labyrinth seal clearance to allow the determined amount of cooling air not passing through the angled holes to pass through the labyrinth seal; and forming the angled holes in the diaphragm.
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Specification