Turbine engine rotating cavity anti-vortex cascade
AssigneeUnited Technologies Corporation
InventorsMatthew E. Bintz, Eric W. Malmborg, Charles P. Gendrich
Life of this patent
Estimating the term…
Abstract
A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members are tubular in shape and provide a radially extending passage. The anti-vortex members include an outer end having a circumferential side with an opening in fluid communication with the radial passage.
Claims12
An anti-vortex cascade for a gas turbine engine comprising:
- an annular support providing a rotational axis;
- and
- multiple tubular anti-vortex members mounted circumferentially on the annular support and providing a radially extending passage, each of the anti-vortex members including an outer end portion having a terminal end, and each of the anti-vortex members having a first circumferential side with an opening radially inboard of the terminal end in fluid communication with the radially extending passage, the opening exposed in a circumferential direction to provide an inlet configured to receive flow through the opening from the circumferential direction and into each of the anti-vortex members.
An anti-vortex cascade for a gas turbine engine comprising:
- an annular support providing a rotational axis;
- and
- multiple tubular anti-vortex members mounted circumferentially on the annular support and providing a radially extending passage, wherein each of the anti-vortex members includes a generally circular cross-section, each of the anti-vortex members including a bent outer end portion extending to a terminal end providing an inlet opening in fluid communication with the radially extending passage, and each of the anti-vortex members having a first circumferential side providing an intrados of the bent outer end portion, and a second circumferential side opposite the first circumferential side providing an extrados of the bent outer end portion.
A gas turbine engine rotor drum comprising:
- spaced apart discs providing a cavity between the discs, the discs configured to rotate in a rotational direction about an axis;
- an annular support mounted on at least one of the discs and within the cavity;
- a cascade of anti-vortex members mounted circumferentially on the annular support and providing a radially extending passage, the anti-vortex members including an outer end having a first circumferential side with an opening in fluid communication with the radially extending passage, wherein each of the anti-vortex members includes a base supported at an inner diameter of the annular support and a body extending radially from the base through the annular support and providing the opening;
- a retainer configured to prevent relative rotation of each of the anti-vortex members relative to the annular support, wherein the retainer has spaced apart ends configured to be moveable relative to one another during an installation and removal procedure;
- and
- wherein the annular support includes an aperture arranged between the anti-vortex members configured to permit flow of conditioning air radially inward through the annular support.
Dependencies are inferred from the claim text.