# US 9,518,469 B2 · Gas turbine engine component > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,518,469 B2 - Document ID: US9518469B2 - Status: Granted - Kind: B2 - Application number: 14/033,900 - Filed: 2013-09-23 - Published: 2014-03-27 - Granted: 2016-12-13 - Earliest claimed: 2012-09-26 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce PLC - Inventors: Ian Tibbott; Dougal Richard Jackson - Web page: https://patentgrep.com/patent/US9518469B2 ## CPC - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 5/187: {Convection cooling} - F05D 2260/22141: using fins or ribs - Y10T 29/49336: Blade making - 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 - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes: determining angles α and β of the directions of cooling air flow into the first and Nth rows, respectively; defining a change in angle φ of the direction of cooling air flow between rows as φ=(β−α)/N; and positioning the pedestals such that a line extending forward from the center of each pedestal in the ith row at an angle {α+φ(i−1)} intersects the (i−1)th row at a location which is midway between two neighboring pedestals of the (i−1)th row, i being an integer from 2 to N. ## Claims ### Claim 1 A method of configuring an internally cooled gas turbine engine component, the component including: a line of cooling air discharge holes, an internal cooling channel disposed forward of and extending substantially parallel to the line of discharge holes, an internal feed cavity disposed between the channel and the line of discharge holes for feeding cooling air from the channel to the discharge holes, and a plurality of flow disrupting pedestals extending between opposing sides of the feed cavity, the pedestals being arranged in a number N of rows, which extend substantially parallel to the line of discharge holes, each row of the number N of rows forming flow inlet angles that vary along the length of the rows, a first row of the number N of rows being located closer to an entrance of the feed cavity than an Nth row of the number N of rows, and remaining rows of the number N of rows being spaced between the first row and the Nth row, and the pedestals being spaced apart from each other within each row, the method including: determining the flow inlet angle α of a direction of cooling air flow into the first row at one or more radial positions; determining a flow outlet angle β of the direction of cooling air flow from the Nth row; defining a change in angle φ of the direction of cooling air flow between the rows as φ=(β−α)/N for the one or more radial positions; and starting from row N, positioning the pedestals such that a line extending forward from the centre of each pedestal in the ith row at an angle {α+φ(i−1)} intersects the (i−1)th row at a location which is midway between two neighbouring pedestals of the (i−1)th row, i being an integer from 2 to N. ### Claim 2 (depends on 1) The method according to claim 1, wherein the rows are spaced substantially equal distances apart. ### Claim 3 (depends on 1) The method according to claim 1, wherein the method further includes: determining the number of pedestals in the Nth row such that each pedestal of the Nth row corresponds to a respective one of the discharge holes; and positioning each pedestal of the Nth row such that a line extending rearward from the pedestal at the flow outlet angle β coincides with the centre of the respective discharge hole. ### Claim 4 (depends on 1) The method according to claim 1, wherein N is four or more. ### Claim 5 (depends on 1) The method according to claim 1, wherein the pedestals are each a column of circular cross-section. ### Claim 6 (depends on 1) The method according to claim 1, wherein the pedestals are each a column of racetrack-shaped or elliptical cross-section. ### Claim 7 (depends on 6) The method according to claim 6, wherein the method further includes: orientating the pedestals such that a long axis of the racetrack-shaped or elliptical cross-section of each pedestal is perpendicular to a line extending forward from the centre of each pedestal in the ith row at an angle {α+φ(i−1)}, i being an integer from 1 to N. ### Claim 8 (depends on 1) The method according to claim 1, wherein the value of the flow inlet angle α varies along the length of the first row. ### Claim 9 (depends on 1) The method according to claim 1, wherein the component is a gas turbine aerofoil, the pedestals extending between pressure surface and suction surface sides of the feed cavity. ### Claim 10 (depends on 9) The method according to claim 9, wherein the line of cooling air discharge holes is a line of slots along a trailing edge of the aerofoil. ### Claim 11 (depends on 1) A process for producing an internally cooled gas turbine engine component, the process including: configuring the component by performing the method of claim 1; and manufacturing the configured component. ### Claim 12 (depends on 11) An internally cooled gas turbine engine component produced by the process of claim 11. ### Claim 13 An internally cooled gas turbine engine component, the component comprising: a line of cooling air discharge holes, an internal cooling channel disposed forward of and extending substantially parallel to the line of discharge holes, an internal feed cavity disposed between the channel and the line of discharge holes for feeding cooling air from the channel to the discharge holes, and a plurality of flow disrupting pedestals extending between opposing sides of the feed cavity, the pedestals being arranged in a number N of rows, which extend substantially parallel to the line of discharge holes, each row of the number N of rows forming flow inlet angles that vary along the length of the rows, a first row of the number N of rows being located closer to an entrance of the feed cavity than an Nth row of the number N of rows, remaining rows of the number N of rows being spaced between the first row and the Nth row, and the pedestals being spaced apart from each other within each row, the first row defining a flow inlet angle α of a direction of cooling air flow into the first row at one or more radial positions, the Nth row defining a flow outlet angle β of the direction of cooling air flow from the Nth row, a change in angle φ of the direction of cooling air flow between the rows being defined as φ=(β−α)/N for the one or more radial positions, and the pedestals being positioned such that a line extending forward from the centre of each pedestal in the ith row at an angle {α±φ(i−1)} intersects the (i−1)th row at a location which is midway between two neighbouring pedestals of the (i−1)th row, i being an integer from 2 to N, wherein each pedestal is positioned such that a plurality of streak lines of cooling air advancing on the pedestals split substantially equally to both sides of each pedestal and then substantially completely recombine downstream of each pedestal. ### Claim 14 (depends on 13) The component according to claim 13, wherein the component is a gas turbine aerofoil, the pedestals extending between pressure surface and suction surface sides of the feed cavity. ### Claim 15 (depends on 14) The component according to claim 14, wherein the line of cooling air discharge holes is a line of slots along a trailing edge of the aerofoil.