# US 2014/0193273 A1 · Interior configuration for turbine rotor blade > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0193273 A1 - Document ID: US20140193273A1 - Status: Published application - Kind: A1 - Application number: 13/737,031 - Filed: 2013-01-09 - Published: 2014-07-10 - Earliest claimed: 2013-01-09 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Harrish Bommanakatte; Jalindar Appa Walunj; Anthony Louis Giglio; Jason Douglas Herzlinger - Web page: https://patentgrep.com/patent/US20140193273A1 ## CPC - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - F01D 5/187: {Convection cooling} - F05D 2240/303: related to the leading edge of a rotor blade - F05D 2260/201: by impingement of a fluid - 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 interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered. ## Claims ### Claim 1 An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine, the interior cooling configuration comprising: a first flow passage and a second flow passage that comprise a side-by-side configuration for a segment; and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage, wherein the crossover passages are staggered. ### Claim 2 (depends on 1) The interior cooling configuration according to claim 1, wherein the blade comprises a turbine rotor blade; and wherein the crossover passages are spaced at longitudinal increments within the segment of the side-by-side configuration. ### Claim 3 (depends on 2) The interior cooling configuration according to claim 2, wherein each of the crossover passages connect to the first flow passage at a port; wherein the crossover passages are staggered such that the ports of the first flow passage are staggered about a linear reference axis that extends longitudinally on an inner wall of the first flow passage. ### Claim 4 (depends on 2) The interior cooling configuration according to claim 2, wherein a reference plane bisects the first flow passage and the second flow passage; wherein the reference plane is a straight plane; and wherein the crossover passages are staggered relative to the reference plane. ### Claim 5 (depends on 4) The interior cooling configuration according to claim 4, wherein the first flow passage includes a facing inner wall that faces the second flow passage, and the second flow passage includes a facing inner wall that faces the first flow passage; wherein each of the crossover passages comprise a linear configuration; and wherein the reference plane bisects the facing inner wall of each of the first flow passage and the second flow passage. ### Claim 6 (depends on 5) The interior cooling configuration according to claim 5, wherein the reference plane is a curved plane that is defined relative to a dimension of the airfoil that varies within the segment. ### Claim 7 (depends on 6) The interior cooling configuration according to claim 6, wherein the reference plane is defined relative to a position of at least one of a pressure sidewall and a suction sidewall of the airfoil. ### Claim 8 (depends on 5) The interior cooling configuration according to claim 5, wherein the reference plane is a curved plane that is defined relative to a dimension of the first flow passage and the second flow passage that varies within the segment. ### Claim 9 (depends on 8) The interior cooling configuration according to claim 8, wherein the reference plane is defined relative to a width of the facing inner wall of each of the first flow passage and the second flow passage. ### Claim 10 (depends on 8) The interior cooling configuration according to claim 8, wherein the reference plane is defined relative to a centerline of the facing inner wall of each of the first flow passage and the second flow passage. ### Claim 11 (depends on 2) The interior cooling configuration according to claim 2, wherein the segment includes a multitude of crossover passages which are longitudinally spaced at regular intervals. ### Claim 12 (depends on 11) The interior cooling configuration according to claim 11, wherein the first flow passage is configured in the airfoil to extend radially between a first end positioned near an inboard boundary of the airfoil and a second end positioned near an outboard boundary of the airfoil; wherein the second flow passage is configured within the airfoil to extend radially between a first end positioned near an inboard boundary of the airfoil and a second end positioned near an outboard boundary of the airfoil; and wherein the second flow passage connects to a supply passage which is configured to receive a flow of coolant through a root of the rotor blade during operation. ### Claim 13 (depends on 12) The interior cooling configuration according to claim 12, wherein the first flow passage is approximately parallel to the second flow passage, both of which extend in a general radial direction; wherein each of the crossover passages is approximately perpendicular to both the first flow passage and the second flow passage; and wherein each of the crossover passages is configured to impinge a coolant flow during operation. ### Claim 14 (depends on 4) The interior cooling configuration according to claim 4, further comprising at least two groupings of five consecutive crossover passages; wherein staggered relative to the reference plane comprises at least one crossover passage in each of the two groupings having a position removed to a first side of the reference plane. ### Claim 15 (depends on 14) The interior cooling configuration according to claim 14, wherein staggered relative to the reference plane comprises at least one crossover passage in each of the two groupings having a position removed to a second side of the reference plane. ### Claim 16 (depends on 15) The interior cooling configuration according to claim 15, wherein staggered relative to the reference plane comprises at least one crossover passage in each of the two groupings having a position that intersects the reference plane. ### Claim 17 (depends on 14) The interior cooling configuration according to claim 14, wherein the crossover passages comprise a non-symmetrical cross-sectional shape; and wherein the staggered relative to the reference plane comprises at least two crossover passages in the each of the two groupings having a differing angular orientation relative to the reference plane. ### Claim 18 An interior cooling configuration formed within an airfoil of a rotor blade of a combustion turbine engine, the interior cooling configuration comprising: a first flow passage and a second flow passage extending radially and in parallel within a segment between an inboard position and an outboard position; and multiple lateral crossover passages extending linearly between and fluidly connecting the first flow passage to the second flow passage, the crossover passages being spaced at regular radial intervals within the segment; wherein a reference plane bisects the first flow passage and the second flow passage; wherein the crossover passages are staggered relative to the reference plane. ### Claim 19 (depends on 18) The interior cooling configuration according to claim 18, wherein the reference plane is a curved plane that is defined relative to a dimension of the airfoil that varies within the segment; wherein the inboard position is near a platform and the outboard position is near an outboard tip of the airfoil; wherein the second flow passage connects to a supply passage which is configured to receive a flow of coolant through a root of the rotor blade during operation. ### Claim 20 (depends on 18) The interior cooling configuration according to claim 18, wherein the first flow passage comprises a leading edge flow passage that parallels in proximity a leading edge of the airfoil; wherein the inboard position is near a platform and the outboard position is near an outboard tip of the airfoil; further comprising at least two groupings of five consecutive crossover passages; wherein staggered relative to the reference plane comprises at least one crossover passage in each of the two groupings having a position removed to a first side of the reference plane and at least one crossover passage in each of the two groupings having a position removed to a second side of the reference plane. ### Claim 21 (depends on 19) The interior cooling configuration according to claim 19, wherein the first flow passage comprises a trailing edge flow passage that parallels in proximity a trailing edge of the airfoil; wherein the inboard position is near a platform and the outboard position is near an outboard tip of the airfoil; further comprising at least two groupings of five consecutive crossover passages; wherein staggered relative to the reference plane comprises at least one crossover passage in each of the two groupings having a position removed to a first side of the reference plane and at least one crossover passage in each of the two groupings having a position removed to a second side of the reference plane. ### Claim 22 (depends on 19) The interior cooling configuration according to claim 19, wherein the reference plane is defined via a plurality of airfoil camber lines within the segment.