# US 11,306,655 B2 · Turbine engine component and method of cooling > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,306,655 B2 - Document ID: US11306655B2 - Status: Granted - Kind: B2 - Application number: 16/356,595 - Filed: 2019-03-18 - Published: 2020-09-24 - Granted: 2022-04-19 - Earliest claimed: 2019-03-18 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Daniel Endecott Osgood; Jonathan Russell Ratzlaff; Kirk D. Gallier - Web page: https://patentgrep.com/patent/US11306655B2 ## CPC - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F02C 7/052: with dust-separation devices - B01D 45/16: generated by the winding course of the gas stream {, the centrifugal forces being generated solely or partly by mechanical means, e.g. fixed swirl vanes} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/12: Cooling - F01D 25/32: Collecting of condensation water; Drainage {; Removing solid particles} - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F05D 2260/601: using an ejector or a jet pump - F05D 2260/607: Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - B01D: SEPARATION (separating solids from solids by wet methods B03B, B03D; by pneumatic jigs or tables B03B; by other dry methods B07; magnetic or electrostatic separation of solid materials from solid materials or fluids, separation by high-voltage electric fields B03C; centrifuges, vortex apparatus B04; presses per se for squeezing-out liquid from liquid-containing material B30B9/02; treatment of water C02F, e.g. softening by ion-exchange C02F1/42; {arrangements of air intake cleaners in gas turbine plants F02C7/05} ; arrangements or mounting of filters in air-conditioning, air-humidification or ventilation F24F13/28) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A component for a turbine engine includes a body having a wall at least partially defining an interior and separating a combustion air flow path from a cooling air flow path. The component also includes at least one fluid inlet supplying cooling air to the interior of the body, as well as a cyclone separator. ## Claims ### Claim 1 A turbine engine comprising: a core comprising a compressor section, a combustion section, and a turbine section, which are axially arranged to define a combustion air flow path passing through the core; a casing surrounding the core; an annulus defined between the core and the casing; a plurality of components with corresponding fluid inlets circumferentially spaced about the annulus; a cooling air flow path passing through at least one of the core and the casing; and a set of cyclone separators within the annulus, each cyclone separator in the set having a cooling air inlet fluidly coupled to the cooling air flow path, a clean air outlet, and a dirty air outlet, wherein the set of cyclone separators includes groups of at least two cyclone separators, each in the group having their clean air outlets fluidly coupled to a common fluid inlet. ### Claim 2 (depends on 1) The turbine engine of claim 1 wherein the common fluid inlet comprises at least one of a plenum, cavity, isolation chamber, or fluid passage. ### Claim 3 (depends on 1) The turbine engine of claim 1 wherein the at least two cyclone separators in the group are circumferentially located on opposite sides of the common fluid inlet. ### Claim 4 (depends on 1) The turbine engine of claim 1 wherein the plurality of components comprises a plurality of airfoils, with the common fluid inlet fluidly coupled to an interior of at least one of the plurality of airfoils. ### Claim 5 (depends on 4) The turbine engine of claim 4 wherein the plurality of airfoils and the set of cyclone separators are circumferentially arranged such that at least one airfoil is positioned between circumferentially adjacent cyclone separators. ### Claim 6 (depends on 4) The turbine engine of claim 4 wherein at least one of the at least two cyclone separators is positioned between circumferentially adjacent airfoils. ### Claim 7 (depends on 4) The turbine engine of claim 4 wherein the common fluid inlet is positioned between circumferentially adjacent airfoils. ### Claim 8 (depends on 4) The turbine engine of claim 4 wherein the plurality of airfoils extend between circumferential outer bands and inner bands. ### Claim 9 (depends on 8) The turbine engine of claim 8 wherein at least some of the set of cyclone separators are radially adjacent one of the outer or inner bands. ### Claim 10 (depends on 9) The turbine engine of claim 9 wherein the at least some of the multiple cyclone separators are positioned between the outer band and the casing. ### Claim 11 (depends on 4) The turbine engine of claim 4 wherein the plurality of airfoils comprise a plurality of stationary vanes. ### Claim 12 (depends on 11) The turbine engine of claim 11 wherein the plurality of stationary vanes comprise a plurality of stationary vanes in the turbine section. ### Claim 13 A component for a turbine engine generating a combustion air flow path and providing a cooling air flow path, the component comprising: a body having a wall extending into the combustion air flow path and at least partially defining an interior and the wall separating the combustion air flow path from the cooling air flow path; at least one fluid inlet supplying cooling air to the interior of the body; and at least two cyclone separators each having a cooling air inlet fluidly coupled to the cooling air flow path, a clean air outlet fluidly coupled to the at least one fluid inlet, and a dirty air outlet. ### Claim 14 (depends on 13) The component of claim 13 further comprising an airfoil body extending between an outer band and an inner band, wherein the at least two cyclone separators are coupled to one of the outer band or the inner band. ### Claim 15 (depends on 14) The component of claim 14 wherein the outer band is coupled to one of the at least two cyclone separators, and the inner band is coupled to another of the at least two cyclone separators. ### Claim 16 (depends on 14) The component of claim 14 wherein a clean air outlet of a first cyclone separator is fluidly coupled to a clean air outlet of a second cyclone separator via at least one cooling passage. ### Claim 17 (depends on 16) The component of claim 16 wherein the at least one cooling passage supplies at least one interior cooling passage within the interior of the airfoil body. ### Claim 18 A method of cooling a component for a turbine engine generating a hot airflow and providing a cooling airflow, with the component confronting the hot airflow and including a wall at least partially defining an interior receiving the cooling airflow, the method comprising: flowing cooling air through a first cyclone separator located within the component to define a cleaned first supply of cooling air; flowing cooling air through a second cyclone separator located within the same component to define a cleaned second supply of cooling air; and directing the cleaned first and second supplies of cooling air to a common interior cooling passage within the interior for the same component. ### Claim 19 (depends on 18) The method of claim 18 further comprising combining the cleaned first and second supplies of cooling air within a common conduit prior to the directing. ### Claim 20 (depends on 18) The method of claim 18 wherein the component further comprises an airfoil body extending between an inner band coupled to the first cyclone separator and an outer band coupled to the second cyclone separator.