# US 2024/0200458 A1 · Hollow airfoil construction using cover subassembly > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2024/0200458 A1 - Document ID: US20240200458A1 - Status: Published application - Kind: A1 - Application number: 18/498,147 - Filed: 2023-10-31 - Published: 2024-06-20 - Earliest claimed: 2022-12-20 - Assignees: Rtx Corporation - Applicants: RTX Corporation - Inventors: John T. Pickens - Web page: https://patentgrep.com/patent/US20240200458A1 ## CPC - F01D 5/18: Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - F01D 9/044: {permanently, e.g. by welding, brazing, casting or the like} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F05D 2230/232: by welding - F05D 2230/50: Building or constructing in particular ways - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A component for a gas turbine engine includes an airfoil having a plurality of channels with a main body extending between a leading edge and a trailing edge. The main body forms a portion of one side of the airfoil and the entirety of an opposing side of the airfoil. A cover is secured to the main body about a perimeter by a weld. The cover extends across a majority of the one side of the airfoil. A plurality of ribs extends from the cover in a direction toward the main body to define the channels. The ribs are secured to an inner surface of the main body by an adhesive. A gas turbine engine and a method are also disclosed. ## Claims ### Claim 1 A component for a gas turbine engine comprising: an airfoil having a plurality of channels with (i) a main body extending between a leading edge and a trailing edge, said main body forming a portion of one side of the airfoil and the entirety of an opposing side of the airfoil; (ii) a cover secured to said main body about a perimeter by a weld, said cover extending across a majority of the one side of the airfoil; and (iii) a plurality of ribs extending from the cover in a direction toward the main body to define the channels, said ribs being secured to an inner surface of the main body by an adhesive, said ribs have an enlarged surface at one of said inner surface of said main body and the cover. ### Claim 2 (depends on 1) The component as set forth in claim 1, wherein the ribs and cover are formed integrally. ### Claim 3 (depends on 1) The component as set forth in claim 1, wherein the ribs and cover are formed separately, and the ribs are brazed to the cover before being secured to the main body through the adhesive. ### Claim 4 (depends on 1) The component as set forth in claim 1, wherein adhesive is also provided in one of said channels between a pair of said ribs, and on said inner surface of said main body. ### Claim 5 (depends on 1) The component as set forth in claim 1, wherein the enlarged surface is at each of said inner surface of said main body and the cover. ### Claim 6 (depends on 1) The component as set forth in claim 1, wherein the inner surface of the main body that is contacted by the ribs is a flat surface. ### Claim 7 A gas turbine engine comprising: a fan for delivering air into a bypass duct and for delivering air into a compressor section; a combustor downstream of the compressor section and a turbine section downstream of the combustor section; the fan, the compressor section and the turbine section each including a plurality of components having airfoils; one type of said airfoils having a plurality of channels with (i) a main body extending between a leading edge and a trailing edge, said main body forming a portion of one side of the airfoil and the entirety of an opposing side of the airfoil; (ii) a cover secured to said main body about a perimeter by a weld, said cover extending across a majority of one side of the airfoil; and (iii) a plurality of ribs extending from the cover in a direction toward the main body to define the channels said ribs being secured to an inner surface of the main body by an adhesive, said ribs have an enlarged surface at one of said inner surface of said main body and the cover. ### Claim 8 (depends on 7) The gas turbine engine as set forth in claim 7, wherein the ribs and cover are formed integrally. ### Claim 9 (depends on 7) The gas turbine engine as set forth in claim 7, wherein the ribs and cover are formed separately, and the ribs are then brazed to the cover before being secured to the main body through the adhesive. ### Claim 10 (depends on 7) The gas turbine engine as set forth in claim 7, wherein adhesive is also provided in one of said channels that extends between a pair of said ribs, and on said inner surface of said main body. ### Claim 11 (depends on 7) The gas turbine engine as set forth in claim 7, wherein the enlarged surface is at each of said inner surface of said main body and the cover. ### Claim 12 (depends on 7) The gas turbine engine as set forth in claim 7, wherein the inner surface of the main body that is contacted by the ribs is a flat surface. ### Claim 13 (depends on 7) The gas turbine engine as set forth in claim 7, wherein said one type of the airfoils is fan blades. ### Claim 14 (depends on 7) The gas turbine engine as set forth in claim 7, wherein said one type of the airfoils is variable vanes in the compressor section. ### Claim 15 A method of forming a hollow airfoil comprising the steps of: 1) forming a cover and rib subassembly having at least a plurality of ribs extending from the cover in a first direction; 2) depositing adhesive on an inner surface of a main body; 3) moving the subassembly such that the ribs move into contact with the adhesive to be secured to the main body; 4) welding around a periphery of the cover to secure it to the main body after step 3); and wherein the ribs have an enlarged surface at one of said inner surface of said main body and the cover. ### Claim 16 (depends on 15) The method as set forth in claim 15, wherein an additive manufacturing technique is utilized to form at least one of the cover, ribs and main body. ### Claim 17 (depends on 15) The method as set forth in claim 15, wherein the cover and ribs are formed integrally in step 1. ### Claim 18 (depends on 15) The method as set forth in claim 15, wherein the ribs are formed separately from the cover and then secured to the cover as part of step 1). ### Claim 19 (depends on 18) The method as set forth in claim 18, wherein the ribs are secured to the cover by a brazing process. ### Claim 20 (depends on 15) The method as set forth in claim 15, wherein the enlarged surface is at both of said inner surface of said main body and the cover.