# US 8,739,548 B2 · Sliding ramp nozzle system for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,739,548 B2 - Document ID: US8739548B2 - Status: Granted - Kind: B2 - Application number: 11/960,936 - Filed: 2007-12-20 - Published: 2009-06-25 - Granted: 2014-06-03 - Earliest claimed: 2007-12-20 - Assignees: United Technologies Corporation - Applicants: Dale William Petty - Inventors: Dale William Petty - Web page: https://patentgrep.com/patent/US8739548B2 ## CPC - F02K 1/386: {mixing devices in the jet pipe, e.g. for mixing primary and secondary flow} - F02K 1/825: {Infrared radiation suppressors} - F02K 3/075: controlling flow ratio between flows - F02K 3/077: the plant being of the multiple flow type, i.e. having three or more flows - F05D 2270/051: Thrust - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A regulator system includes a slidable ramp intermediate a secondary flow path and a primary flow path of a gas turbine engine nozzle section. ## Claims ### Claim 1 A jet area regulator system for a gas turbine engine comprising: a ramp adjacent a secondary flow path for a secondary flow and a primary flow path for a primary flow, said ramp axially slidable to regulate said secondary flow, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp, and wherein said ramp is downstream of a planar primary nozzle of said primary flow path. ### Claim 2 (depends on 1) The system as recited in claim 1, further comprising an actuator system which axially slides said ramp parallel to a longitudinal axis of the gas turbine engine with respect to a passage in communication with said secondary flow path. ### Claim 3 (depends on 1) The system as recited in claim 1, wherein said ramp is pressure balanced to a reference pressure. ### Claim 4 (depends on 1) The system as recited in claim 1, wherein a passage in communication with said secondary flow path is transverse to a longitudinal axis of said engine, said ramp axially slidable with respect to said passage to regulate said secondary flow therethrough. ### Claim 5 (depends on 1) The system as recited in claim 1, wherein said secondary flow is selectively sourced from a fan section of the gas turbine engine. ### Claim 6 (depends on 1) The system as recited in claim 1, wherein said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine. ### Claim 7 (depends on 6) The system as recited in claim 6 wherein said secondary flow includes a variable cycle third stream fan flow selectively sourced from a fan section of the gas turbine engine. ### Claim 8 (depends on 6) The system as recited in claim 6 wherein said secondary flow is selectively sourced from a fan section of the gas turbine engine. ### Claim 9 (depends on 1) The system as recited in claim 1, wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from a compressor section. ### Claim 10 (depends on 1) The system as recited in claim 1, wherein said plenum is downstream, relative to said secondary flow, of said ramp. ### Claim 11 (depends on 1) The system as recited in claim 1, wherein said plenum urges said ramp upstream, relative to said secondary flow. ### Claim 12 A nozzle section for a gas turbine engine comprising: a secondary flow duct with a generally planar secondary nozzle to communicate a secondary flow therethrough; a primary flow duct with a generally planar primary nozzle to communicate primary flow therethrough, said generally planar primary nozzle adjacent to said generally planar secondary nozzle; a ramp axially slidable relative to a passage in communication with said secondary flow path to regulate said secondary flow though said passage, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp; and wherein said primary duct is generally circular in cross-section at an upstream segment and transitions into said planar primary nozzle at a downstream segment. ### Claim 13 (depends on 12) The nozzle section as recited in claim 12, wherein said ramp is pressure balanced to a reference pressure. ### Claim 14 (depends on 12) The nozzle section as recited in claim 12, wherein said secondary duct is bifurcated. ### Claim 15 (depends on 14) The nozzle section as recited in claim 14, wherein said bifurcated secondary duct joins at said secondary nozzle. ### Claim 16 (depends on 12) The nozzle section as recited in claim 12, wherein said passage is downstream of said planar primary nozzle. ### Claim 17 (depends on 12) The nozzle section as recited in claim 12, wherein said ramp is transverse to a longitudinal axis of the gas turbine engine. ### Claim 18 (depends on 12) The nozzle section as recited in claim 12, wherein said generally planar secondary nozzle is downstream of said generally planar primary nozzle. ### Claim 19 (depends on 12) The nozzle section as recited in claim 12, wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from said fan section. ### Claim 20 (depends on 12) The nozzle section as recited in claim 12, wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from a compressor section. ### Claim 21 A gas turbine engine comprising: an engine duct structure and an inner structure which at least partially define a secondary flow path for a secondary flow and a primary flow path for a primary flow, said secondary flow path defined at least partially around a perimeter of said primary flow path; a secondary flow duct with a generally planar secondary nozzle to communicate said secondary flow therethrough; a primary flow duct with a generally planar primary nozzle to communicate said primary flow therethrough, said generally planar primary nozzle adjacent said generally planar secondary nozzle; a ramp axially slidable relative to a passage in communication with said secondary flow path to regulate said secondary flow though said passage, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp; and wherein said primary duct is generally circular in cross-section at an upstream segment and transitions into said planar primary nozzle at a downstream segment. ### Claim 22 (depends on 21) The engine as recited in claim 21, wherein said secondary duct is bifurcated. ### Claim 23 A jet area regulator system for a gas turbine engine comprising: a ramp adjacent a secondary flow path for a secondary flow and a primary flow path for a primary flow, said ramp axially slidable to regulate said secondary flow, said ramp adjacent to a plenum to facilitate a pressure balance of said ramp, said plenum downstream of said ramp; and wherein said secondary flow is selectively sourced only from a fan section of the gas turbine engine and said primary flow includes at least a combustion core gas exhaust flow sourced from a turbine section of the gas turbine engine and a flow from said fan section.