# US 12,180,890 B1 · Variable bleed valve assemblies > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,180,890 B1 - Document ID: US12180890B1 - Status: Granted - Kind: B1 - Application number: 18/454,531 - Filed: 2023-08-23 - Published: 2024-12-26 - Granted: 2024-12-31 - Earliest claimed: 2023-06-23 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Nageswar Rao Ganji; Ravindra Shankar Ganiger; Ambika Shivamurthy; Hiranya Kumar Nath; Trevor H. Wood - Web page: https://patentgrep.com/patent/US12180890B1 ## CPC - F02C 7/00: Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) - F02C 6/08: the gas being bled from the gas-turbine compressor - F02C 7/045: having provisions for noise suppression - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F05D 2260/96: Preventing, counteracting or reducing vibration or noise - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract Example variable bleed valve assemblies for a gas turbine engine are disclosed herein, including a port extending radially outward from a compressor section of the gas turbine engine, the port defining a variable bleed valve cavity, the port to resonate at a resonant frequency based on an operating condition of the gas turbine engine, and an acoustic suppressor positioned on a wall of the port, the acoustic suppressor extending circumferentially along the wall by a length greater than a cross-sectional width of the acoustic suppressor, the acoustic suppressor defining a resonant cavity based on the length and the cross-sectional width, the acoustic suppressor including a perforated portion, the acoustic suppressor tuned to resonate at the resonant frequency based on the length and the perforated portion. ## Claims ### Claim 1 A variable bleed valve assembly for a gas turbine engine, comprising: a port extending radially outward from a compressor section of the gas turbine engine, the port defining a variable bleed valve cavity, the port to resonate at a resonant frequency based on an operating condition of the gas turbine engine, the port including a wall; and a first partition extending from the wall; a second partition extending from the wall; and an acoustic suppressor positioned on the wall of the port, the acoustic suppressor having a length extending along the wall, the length extending between the first partition and the second partition, the length greater than a cross-sectional width of the acoustic suppressor, the acoustic suppressor defining a resonant cavity based on the length and the cross-sectional width, the acoustic suppressor including a perforated portion positioned along a first dimension of the length and a non-perforated portion positioned along a second dimension of the length, the acoustic suppressor tuned to resonate at the resonant frequency based on the length and the perforated portion, a sum of the first dimension and the second dimension equal to the length. ### Claim 2 (depends on 1) The variable bleed valve assembly of claim 1, wherein the acoustic suppressor is a first acoustic resonator, and the resonant cavity is a first resonant cavity, further including a second acoustic resonator positioned on the wall adjacent to the first acoustic resonator, the second acoustic resonator including a second resonant cavity. ### Claim 3 (depends on 2) The variable bleed valve assembly of claim 2, wherein the first acoustic resonator is coupled to the second acoustic resonator, further including a dividing wall positioned between the first resonant cavity and the second resonant cavity. ### Claim 4 (depends on 3) The variable bleed valve assembly of claim 3, wherein the second acoustic resonator extends along a curved length, the length of the first acoustic resonator different than the curved length, the curved length having a component parallel to a radial axis of the gas turbine engine. ### Claim 5 (depends on 2) The variable bleed valve assembly of claim 2, the second acoustic resonator including a second perforated portion positioned along a third dimension different than the first dimension. ### Claim 6 (depends on 1) The variable bleed valve assembly of claim 1, wherein the acoustic suppressor is a first acoustic resonator, further including a contoured surface defining a plurality of acoustic resonators including the first acoustic resonator. ### Claim 7 (depends on 6) The variable bleed valve assembly of claim 6, wherein the contoured surface is coupled to the wall of the port. ### Claim 8 (depends on 6) The variable bleed valve assembly of claim 6, wherein the contoured surface and the wall of the port are a single unified part. ### Claim 9 (depends on 1) The variable bleed valve assembly of claim 1, wherein the acoustic suppressor includes a ridge positioned between a first valley and a second valley, the first valley upstream of the second valley relative to a bleed flow path of the port, the perforated portion positioned between the ridge and the second valley. ### Claim 10 (depends on 9) The variable bleed valve assembly of claim 9, wherein the perforated portion includes a plurality of circular holes positioned in an array pattern. ### Claim 11 A gas turbine engine, comprising: a compressor section; and a variable bleed valve including: a door actuatable between a closed position and an opened position; a port having a first wall and a second wall extending radially outward between the compressor section and the door, the first wall and the second wall defining a cavity and a bleed flow path between the compressor section and the door; a first partition extending from the first wall; and a second partition extending from the first wall; a first plurality of acoustic suppressors coupled to the first wall, the first plurality of acoustic suppressors including an acoustic resonator having a length extending along the first wall, the length extending between the first partition and the second partition, the acoustic resonator including a perforated portion positioned along a first dimension of the length and a non-perforated portion positioned along a second dimension of the length, a sum of the first dimension and the second dimension equal to the length; and a second plurality of acoustic suppressors coupled to the second wall. ### Claim 12 (depends on 11) The gas turbine engine of claim 11, wherein the acoustic resonator is a first acoustic resonator, the first plurality of acoustic suppressors further includes and a second acoustic resonator, the first acoustic resonator and the second acoustic resonators tuned to a resonant frequency. ### Claim 13 (depends on 11) The gas turbine engine of claim 11, wherein the acoustic resonator is a first acoustic resonator, the first plurality of acoustic suppressors further includes and a second acoustic resonator, the first acoustic resonator tuned to a first resonant frequency, the second acoustic resonator tuned to a second resonant frequency different than the first resonant frequency. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the the perforated portion is a first perforated portion, the non-perforated portion is a first non-perforated portion, and the second acoustic resonator includes a second perforated portion positioned along the first dimension and a second non-perforated portion positioned along a curved length, the curved length greater than the second dimension and the first dimension. ### Claim 15 (depends on 13) The gas turbine engine of claim 13, wherein the first acoustic resonator includes a first pattern of perforations, the second acoustic resonator including a second pattern of perforations different than the first pattern of perforations. ### Claim 16 An aircraft, comprising: a gas turbine engine including a booster section and a high-pressure compressor section; and a variable bleed valve assembly positioned between the booster section and the high-pressure compressor section, the variable bleed valve assembly including: a port defining a bleed flow path, the port including a wall; a first partition extending from the wall; a second partition extending from the wall; and a acoustic resonator coupled to the wall of the port, the acoustic resonator including a ridge and a plurality of perforations, the ridge defining a resonant cavity, the acoustic resonator having a length extending along the wall, the length extending between the first partition and the second partition, the acoustic resonator including a perforated portion positioned along a first dimension of the length and a non-perforated portion positioned along a second dimension of the length, a sum of the first dimension and the second dimension equal to the length. ### Claim 17 (depends on 16) The aircraft of claim 16, including a contoured surface coupled to the wall of the port, the contoured surface including a first valley, a second valley, and the ridge defining the acoustic resonator, the first valley positioned downstream of the ridge and the second valley positioned upstream of the ridge relative to the bleed flow path. ### Claim 18 (depends on 17) The aircraft of claim 17, wherein the plurality of perforations is positioned between the ridge and the second valley. ### Claim 19 (depends on 17) The aircraft of claim 17, wherein the plurality of perforations is a first plurality of perforations positioned between the first valley and the ridge, further including a second plurality of perforations positioned between the ridge and the second valley. ### Claim 20 (depends on 17) The aircraft of claim 17, wherein the length includes at least two 90 degree turns.