# US 8,465,252 B2 · Turbine engine rotating cavity anti-vortex cascade > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,465,252 B2 - Document ID: US8465252B2 - Status: Granted - Kind: B2 - Application number: 12/577,783 - Filed: 2009-10-13 - Published: 2010-10-21 - Granted: 2013-06-18 - Earliest claimed: 2009-04-17 - Assignees: United Technologies Corporation - Applicants: Matthew E. Bintz; Eric W. Malmborg; Charles P. Gendrich - Inventors: Matthew E. Bintz; Eric W. Malmborg; Charles P. Gendrich - Web page: https://patentgrep.com/patent/US8465252B2 ## CPC - F02C 6/08: the gas being bled from the gas-turbine compressor - F01D 5/087: {in the radial passages of the rotor disc} - F01D 25/12: Cooling - F04D 29/321: {for axial flow compressors} - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) ## 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The anti-vortex cascade according to claim 1, wherein the radially extending passage extends along and coaxially with a radial axis. ### Claim 3 (depends on 2) The anti-vortex cascade according to claim 2, wherein the annular support includes an aperture arranged between each of the anti-vortex members configured to permit flow of conditioning air radially inward through the annular support. ### Claim 4 (depends on 1) The anti-vortex cascade according to claim 1, wherein the annular support includes an outer diameter, the opening extending from a location near the outer diameter to the terminal end of each of the anti-vortex members. ### Claim 5 (depends on 1) The anti-vortex cascade according to claim 1, 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. ### Claim 6 (depends on 5) The anti-vortex cascade according to claim 5, comprising a retainer configured to prevent relative rotation of each of the anti-vortex members relative to the annular support. ### Claim 7 (depends on 6) The anti-vortex cascade according to claim 6, wherein the base includes a flat and the retainer is arranged adjacent to the flat and configured to block rotation of each of the anti-vortex members about a radial axis. ### Claim 8 (depends on 6) The anti-vortex cascade according to claim 6, wherein the retainer has spaced apart ends configured to be moveable relative to one another during an installation and removal procedure. ### Claim 9 (depends on 5) The anti-vortex cascade according to claim 5, wherein the annular support includes an annular groove having a lip, the base supported within the annular groove preventing relative radial movement of each of the anti-vortex members relative to the annular support. ### Claim 10 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. ### Claim 11 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. ### Claim 12 (depends on 11) The rotor drum according to claim 11, wherein the cavity extends a radial length, and the anti-vortex members radially extends from the annular support less than the radial extent of the cavity.