Gas turbine systems involving rotor bayonet coverplates and tools for installing such coverplates
AssigneeUnited Technologies Corporation
InventorsJoseph T. Caprario, Daniel J. Griffin
Life of this patent
Estimating the term…
Abstract
Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.
Claims6
A tool for installing a coverplate on and removing a coverplate from a turbine disk of a gas turbine engine, the coverplate extending axially between an upstream portion and a downstream portion, the tool comprising:
- a body portion;
- upstream and downstream axial compression surfaces operative to be positioned along a range of axial positions relative to each other such that engagement of the axial compression surfaces with a coverplate applies an axial compression load to the coverplate;
- and
- a radial compression surface operative to be positioned along a range of radial positions with respect to the body portion such that engagement of the radial compression surface with the coverplate applies a radial load to the coverplate.
A tool fbr installing a coverplate on and removing a coverplate from a turbine disk of a gas turbine engine, the coverplate extending axially between an upstream portion and a downstream portion, the tool comprising:
- a body portion;
- upstream and downstream axial compression surfaces operative to be positioned along a range of axial positions relative to each other such that engagement of the axial compression surfaces with a coverplate applies an axial compression load to the coverplate;
- and
- a radial compression surface operative to be positioned along a range of radial positions with respect to the body portion such that engagement of the radial compression surface with the coverplate applies a radial load to the coverplate;
- wherein the tool comprises a radial compression jaw;
- wherein the radial compression surface is a surface of the radial compression jaw;
- wherein the body portion defines an annular cavity;
- and
- wherein the radial compression jaw is mounted at least partially within the cavity.
A tool for installing a coverplate on and removing a coverplate from a turbine disk of a gas turbine engine, the coverplate extending axially between an upstream portion and a downstream portion, the tool comprising:
- a body portion;
- upstream and downstream axial compression surfaces operative to be positioned along a range of axial positions relative to each other such that engagement of the axial compression surfaces with a coverplate applies an axial compression load to the coverplate;
- and
- a radial compression surface operative to be positioned along a range of radial positions with respect to the body portion such that engagement of the radial compression surface with the coverplate applies a radial load to the coverplate;
- wherein axial positioning of the axial compression surface is facilitated by a first annular arrangement of bolts extending through the body portion;
- and
- wherein radial positioning of the radial compression surface is facilitated by a second annular arrangement of bolts extending through the body portion.
Dependencies are inferred from the claim text.