# US 11,905,853 B2 · Turbine engine component with a set of deflectors > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,905,853 B2 - Document ID: US11905853B2 - Status: Granted - Kind: B2 - Application number: 17/228,778 - Filed: 2021-04-13 - Published: 2021-12-09 - Granted: 2024-02-20 - Earliest claimed: 2020-06-08 - Assignees: GE Avio S.r.l. - Applicants: GE Avio S.r.l. - Inventors: Alberto Buonvino; Luca Giacobone; Daniele Coutandin; Ernesto Sozio; Francesco Bertini - Web page: https://patentgrep.com/patent/US11905853B2 ## CPC - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 5/14: Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour} - F01D 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)} - F01D 11/001: {for sealing space between stator blade and rotor} - F01D 11/006: {Sealing the gap between rotor blades or blades and rotor} - F01D 11/04: using sealing fluid, e.g. steam - F01D 5/146: {of blades with tandem configuration, split blades or slotted blades} - F05D 2220/32: in gas turbines - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/126: Baffles or ribs - F05D 2240/129: Cascades, i.e. assemblies of similar profiles acting in parallel - F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor - F05D 2250/44: by counter rotation - 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) - 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 An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path. ## Claims ### Claim 1 An airfoil assembly defining a primary airflow path for a turbine engine, the airfoil assembly comprising: a platform at least partially defining a secondary airflow path fluidly coupled to the primary airflow path, the platform having an upper platform face at least partially defining the primary airflow path; an airfoil extending from the platform and into the primary airflow path, the airfoil having an airfoil outer wall defining an airfoil pressure side and an airfoil suction side; and a deflector provided along a portion of the platform axially forward of the airfoil, the deflector extending into the secondary airflow path, the deflector having: an axially forward edge provided within the secondary airflow path; an axially aft edge provided upstream of the axially forward edge; and a deflector wall defining a concave side and a convex side and extending between an axially forward edge and an axially aft edge; wherein the deflector is oriented such that the concave side corresponds to the airfoil pressure side. ### Claim 2 (depends on 1) The airfoil assembly of claim 1, wherein the deflector reduces at least one dimension of a cross-sectional area of the secondary airflow path at the deflector to form a reduced cross-sectional area. ### Claim 3 (depends on 2) The airfoil assembly of claim 2, wherein a local cross-sectional area of the secondary airflow path at a platform inlet is greater than the reduced cross-sectional area. ### Claim 4 (depends on 2) The airfoil assembly of claim 2, wherein a local cross-sectional area of the secondary airflow path at a platform inlet is less than the reduced cross-sectional area. ### Claim 5 (depends on 1) The airfoil assembly of claim 1, wherein the airfoil is a rotatable blade. ### Claim 6 (depends on 1) The airfoil assembly of claim 1, wherein the deflector turns an airflow within the secondary airflow path from a first circumferential direction to a second circumferential direction, with the second circumferential direction corresponding to a direction of rotation of the airfoil assembly. ### Claim 7 (depends on 1) The airfoil assembly of claim 1, wherein the deflector is included within a plurality of circumferentially spaced deflectors provided along the platform. ### Claim 8 (depends on 1) The airfoil assembly of claim 1, wherein the deflector extends radially outward from the upper platform face. ### Claim 9 A turbine engine comprising: a primary airflow path; an engine centerline; a first airfoil assembly at least partially provided within a primary airflow path of the turbine engine, the first airfoil assembly being rotatable in a first rotational direction, the first airfoil assembly comprising: a platform at least partially defining a secondary airflow path fluidly coupled to the primary airflow path, the platform having an upper platform face at least partially defining the primary airflow path; a first airfoil extending from the platform and into the primary airflow path the first airfoil having an airfoil outer wall defining an airfoil pressure side and an airfoil suction side; and a deflector provided along a portion of the platform axially forward of the first airfoil the deflector extending into the secondary airflow path, the deflector having deflector wall defining a concave side and a convex side, with the deflector being oriented such that the concave side corresponds to the airfoil pressure side of the first airfoil; and a second airfoil assembly at least partially provided within the primary airflow path, the second airfoil assembly comprising a second airfoil provided upstream of and axially adjacent the first airfoil, the second airfoil assembly being rotatable in a second rotational direction that that is counter the first rotational direction. ### Claim 10 A turbine engine comprising: a primary airflow path; a rotor; a first airfoil assembly comprising: a first platform having a first upper platform face at least partially defining the primary airflow path, the first airfoil assembly being radially spaced from the rotor to define a gap therebetween; and a first airfoil extending from the first platform and into the primary airflow path, the first airfoil having an airfoil outer wall defining an airfoil pressure side and an airfoil suction side; a second airfoil assembly comprising: a second airfoil provided upstream of and axially adjacent the first airfoil; and a second platform extending from the rotor; a secondary airflow path at least partially defined by the gap between the first platform and the rotor, and the second platform; and a deflector extending between an axially forward edge and an axially aft edge, the deflector being positioned within the secondary airflow path such that that the axially aft edge is upstream of the axially forward edge. ### Claim 11 (depends on 10) The turbine engine of claim 10, wherein the deflector is provided along a portion of the first upper platform face. ### Claim 12 (depends on 10) The turbine engine of claim 10, wherein the secondary airflow path is formed to channel a leakage airflow from a first region, upstream the first airfoil assembly, to a second region, downstream the first airfoil assembly. ### Claim 13 (depends on 10) The turbine engine of claim 10, wherein an inlet of the secondary airflow path is provided radially between the first platform and the second platform, with at least a portion of the deflector provided within the inlet. ### Claim 14 (depends on 10) The turbine engine of claim 10, wherein the second platform extends axially forward of and axially aft of the second airfoil. ### Claim 15 (depends on 10) The turbine engine of claim 10, wherein the secondary airflow path includes an inlet formed by a gap provided between the first platform and the second platform, with at least a portion of the deflector being provided within the inlet. ### Claim 16 (depends on 15) The turbine engine of claim 15, wherein the deflector is provided radially inward from a respective portion of the second platform forming the inlet.