# US 5,704,763 A · Shear jet cooling passages for internally cooled machine elements > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 5,704,763 A - Document ID: US5704763A - Status: Granted - Kind: A - Application number: 07/561,138 - Filed: 1990-08-01 - Granted: 1998-01-06 - Earliest claimed: 1990-08-01 - Assignees: General Electric Company - Inventors: Ching-Pang Lee - Web page: https://patentgrep.com/patent/US5704763A ## CPC - F01D 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall} - F05D 2250/25: helical - F05D 2260/2212: by creating turbulence - 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 A cooling passageway construction particularly adapted for cooling the interior of a heated turbine engine assembly and/or airfoil blade includes an undulating partition which subdivides the passageway into first and second subpassages. The partition defines localized minimum throat areas within each subpassage to produce localized shear jet flow between the partition and the walls of the passageway. Bleed holes may be formed through the partition to generate additional turbulence within the coolant flow and further enhance heat transfer. ## Claims ### Claim 1 A cooling passageway construction for cooling the interior of a heated machine element or machine assembly, said passageway comprising a partition subdividing said passageway into a first subpassage and a second subpassage, said partition having a wavy configuration defining a series of spaced apart minimum throat areas along said first and second subpassages such that said minimum throat areas defined along said first subpassage are staggered between said minimum throat areas defined along said second subpassage. ### Claim 2 (depends on 1) The construction of claim 1, wherein said partition is formed with a plurality of perforations for allowing fluid communication between said first and second subpassages. ### Claim 3 (depends on 2) The construction of claim 2, wherein said perforations are located adjacent to said minimum throat areas. ### Claim 4 (depends on 2) The construction of claim 2, wherein said perforations are located between said minimum throat areas. ### Claim 5 (depends on 1) The construction of claim 1, further comprising a turbulence generator located between a pair of said minimum throat areas in said first subpassage for preventing boundary layer growth therein. ### Claim 6 (depends on 5) The construction of claim 5, wherein said turbulence generator comprises a rib member projecting from said machine element into said first subpassage. ### Claim 7 (depends on 6) The construction of claim 6, wherein said rib member extends transversely across said first subpassage. ### Claim 8 (depends on 1) The construction of claim 1, wherein said machine element comprises an airfoil. ### Claim 9 (depends on 8) The construction of claim 8, wherein said airfoil comprises a turbine blade. ### Claim 10 A gas turbine engine apparatus constructed with an internal cooling passageway defining a first wall and a second wall, said passageway having a partition extending therethrough so as to divide said passageway into a first subpassage and a second subpassage, said first subpassage having a flowpath cross section extending between said partition and said first wall and said second subpassage having a flowpath cross section extending between said partition and said second wall, said first and second subpassages respectively defining along with said partition, spaced apart minimum flowpath throat areas located between said partition and said first and second walls for producing high velocity flow along said first and second walls and further defining spaced apart low velocity flow sections located between said minimum throat areas and wherein said low velocity flow sections define a larger flowpath section that defined at said minimum throat areas. ### Claim 11 An airfoil blade comprising: an airfoil body having a root portion, a tip portion, a leading edge, a trailing edge and an internal coolant passageway having opposed walls located within said blade, and shear jet flow means provided in said coolant passageway for directing coolant flow through said coolant passageway along said walls in a series of spaced apart, localized high velocity flow jets. ### Claim 12 (depends on 11) The airfoil blade of claim 11, wherein said shear jet means comprises a flow constricting partition separating said coolant passageway into a first subpassage and a second subpassage. ### Claim 13 (depends on 12) The airfoil blade of claim 12, wherein said partition defines a series of spaced apart minimum throat areas within said first subpassage and within said second subpassage for producing said high velocity flow jets. ### Claim 14 (depends on 13) The airfoil blade of claim 13, wherein said partition comprises an undulating profile extending through said passageway such that said minimum throat areas defined within said first subpassage are staggered between said minimum throat areas defined within said second subpassage. ### Claim 15 (depends on 14) The airfoil blade of claim 14, wherein said partition is formed with a plurality of perforations located between said minimum throat areas. ### Claim 16 (depends on 15) The airfoil blade of claim 15, further comprising turbulence generating means projecting into said first subpassage between a pair of said minimum throat areas. ### Claim 17 (depends on 13) The airfoil blade of claim 13, further comprising turbulence generating means projecting into said first subpassage between a pair of said minimum throat areas. ### Claim 18 (depends on 14) The airfoil blade of claim 14, wherein said minimum throat areas extend from said root portion to said tip portion and wherein coolant flows through said minimum throat areas in a direction generally from said leading edge toward said trailing edge. ### Claim 19 (depends on 18) The airfoil blade of claim 18, wherein said undulating profile decreases in size toward said trailing edge. ### Claim 20 (depends on 14) The airfoil blade of claim 14, wherein said minimum throat areas extend from a central portion of said blade toward said trailing edge and wherein coolant flows therethrough in a direction generally from said root portion to said tip portion.