# US 10,865,990 B2 · Nested article by additive manufacturing with non-removable internal supporting structure > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,865,990 B2 - Document ID: US10865990B2 - Status: Granted - Kind: B2 - Application number: 15/816,314 - Filed: 2017-11-17 - Published: 2018-05-24 - Granted: 2020-12-15 - Earliest claimed: 2016-11-18 - Assignees: Ansaldo Energia Switzerland AG - Applicants: Ansaldo Energia Switzerland AG - Inventors: Alexey Stytsenko; Sergey Mylnikov; Igor Baibuzenko; Michael Maurer - Web page: https://patentgrep.com/patent/US10865990B2 ## CPC - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F02C 7/222: {Fuel flow conduits, e.g. manifolds} - F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances} - F23R 3/36: Supply of different fuels - B22F 10/28: Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] - B22F 10/47: characterised by structural features - F05D 2230/31: Layer deposition - F05D 2250/14: elliptical - F05D 2250/16: parabolic - F23R 2900/00018: Manufacturing combustion chamber liners or subparts - F23R 2900/03341: Sequential combustion chambers or burners - Y02P 10/25: Process efficiency - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - 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) - B22F: WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER (making alloys by powder metallurgy C22C); APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02P: CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS ## Abstract An additive manufactured article for a gas turbine having a body with two lateral surfaces elongated in a first direction; at least a nested duct housed within the lateral surfaces and elongated in the first direction; a structure so that the nested duct is structurally connected to an attachment within the lateral surfaces, wherein at least the body, the duct and the structure are manufactured by an additive manufacturing process and the structure includes an array of ribs attached to the duct in order to compensate differential elongation along the first direction of the duct with respect to the attachment of the ribs by flexural deformation. ## Claims ### Claim 1 A fuel injector device for a gas turbine, the fuel injector device comprising: a body having two lateral surfaces extending along a longitudinal direction and a crosswise direction; the body being streamlined for use in a fluid flow and the lateral surfaces joined to one another at an upstream side form a leading edge of the body and the lateral surfaces joined to one another at a downstream side to form a trailing edge of the body; a shell defining a gas fuel plenum, the shell nested within the lateral surfaces, wherein the shell is configured to provide a gas fuel flow into the fluid flow; an oil fuel duct, the oil fuel duct elongated in the longitudinal direction, the oil fuel duct nested within the shell, wherein the oil fuel duct is configured to provide an oil fuel flow into the fluid flow; an array of ribs extending between the shell and the oil fuel duct, wherein the array of ribs are configured to compensate differential elongation of the nested oil fuel duct with respect to the shell along the crosswise direction by flexural deformation; struts supported within the lateral surfaces for supporting the shell; and a cut defined between the struts and a wall structure, the wall structure delimiting a cooling air plenum, wherein the body, the shell and the oil fuel duct are additively manufactured. ### Claim 2 (depends on 1) The fuel injector device according to claim 1, wherein each rib of the array of ribs is thicker close to the oil fuel duct and the shell. ### Claim 3 (depends on 2) The fuel injector device according to claim 2, wherein each rib of the array of ribs is filleted to the oil fuel duct and/or the shell along a parabolic or elliptic profile. ### Claim 4 (depends on 1) The fuel injector device according to claim 1, wherein an aspect ratio of the each rib of the array of ribs is at least 30. ### Claim 5 (depends on 1) The fuel injector device according to claim 1, comprising: a cooling air plenum within the lateral surfaces and upstream of the oil fuel duct and the shell, the cooling air plenum being defined by a wall structure. ### Claim 6 (depends on 5) The fuel injector device according to claim 5, comprising: a carrier air plenum defined within the lateral surfaces by the shell and the wall structure. ### Claim 7 (depends on 1) A gas turbine engine comprising: a combustor; and the fuel injector device according to claim 1. ### Claim 8 (depends on 1) The fuel injector device according to claim 1, wherein the struts are substantially parallel with respect to a transverse direction of the fuel injector device. ### Claim 9 (depends on 1) The fuel injector device according to claim 1, wherein each rib of the array of ribs is wavy. ### Claim 10 (depends on 1) The fuel injector device according to claim 1, wherein the struts are inclined with respect to a transverse direction of the fuel injector device.