# US 10,480,347 B2 · Divided baffle for components of gas turbine engines > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,347 B2 - Document ID: US10480347B2 - Status: Granted - Kind: B2 - Application number: 15/874,070 - Filed: 2018-01-18 - Published: 2019-07-18 - Granted: 2019-11-19 - Earliest claimed: 2018-01-18 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Dominic J. Mongillo, Jr.; Ricardo Trindade; Nicholas M. LoRicco - Web page: https://patentgrep.com/patent/US10480347B2 ## CPC - F01D 25/12: Cooling - 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 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall} - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2240/126: Baffles or ribs - F05D 2260/202: by film cooling - 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 Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities. ## Claims ### Claim 1 A divided baffle for a gas turbine engine, the divided baffle comprising: a baffle body having a first end and a second end; at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities; at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities; and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities. ### Claim 2 (depends on 1) The divided baffle of claim 1, wherein the first feed cavity is defined between the at least one divider and a first portion of the baffle body and the second feed cavity is defined between the at least one divider and a second portion of the baffle body, wherein each of the first portion and the second portion include one or more impingement holes. ### Claim 3 (depends on 1) The divided baffle of claim 1, further comprising at least one flow separator located on an external surface of the baffle body, wherein the at least one flow separator is arranged to at least one of position and support the baffle body within an airfoil cavity. ### Claim 4 (depends on 1) The divided baffle of claim 1, wherein the at least one divider includes a first divider, a second divider, and a third divider, wherein: the first feed cavity is defined between a first portion of the baffle body, the first divider, the second divider, and a first cap located at the first end; the second feed cavity is defined between a second portion of the baffle body, the first divider, the third divider, and a second cap located at the second end; and a third feed cavity defined between a third portion of the baffle body, the second divider, the third divider, and a third cap located at the first end. ### Claim 5 A component for a gas turbine engine, the component comprising: an airfoil having a leading edge, a trailing edge, a suction side, and a pressure side, wherein an airfoil cavity is formed within the airfoil, wherein the airfoil extends from an inner diameter to an outer diameter; and a divided baffle installed within the airfoil cavity, the divided baffle comprising: a baffle body having a first end and a second end, wherein the first end is located proximate the inner diameter and the second end is located proximate the outer diameter; at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities; at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities; and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities. ### Claim 6 (depends on 5) The component of claim 5, wherein the first feed cavity is defined between the at least one divider and a first portion of the baffle body and the second feed cavity is defined between the at least one divider and a second portion of the baffle body, wherein each of the first portion and the second portion include one or more impingement holes. ### Claim 7 (depends on 5) The component of claim 5, further comprising at least one flow separator located on an external surface of the baffle body, wherein the at least one flow separator is arranged to at least one of position and support the baffle body within the airfoil cavity. ### Claim 8 (depends on 7) The component of claim 7, wherein the at least one flow separator is integrally formed with the baffle body. ### Claim 9 (depends on 7) The component of claim 7, wherein the at least one flow separator is integrally formed with the airfoil. ### Claim 10 (depends on 5) The component of claim 5, wherein the at least one divider includes a first divider, a second divider, and a third divider, wherein: the first feed cavity is defined between a first portion of the baffle body, the first divider, the second divider, and a first cap located at the first end; the second feed cavity is defined between a second portion of the baffle body, the first divider, the third divider, and a second cap located at the second end; and a third feed cavity defined between a third portion of the baffle body, the second divider, the third divider, and a third cap located at the first end. ### Claim 11 (depends on 5) The component of claim 5, wherein the airfoil cavity is divided into at least two impingement cavities, wherein the impingement cavities are defined between the baffle body and an interior surface of the airfoil that defines the airfoil cavity. ### Claim 12 (depends on 5) The component of claim 5, wherein the airfoil is a vane of a gas turbine engine. ### Claim 13 (depends on 5) The component of claim 5, wherein the airfoil cavity is a leading edge cavity of the airfoil. ### Claim 14 A gas turbine engine comprising: an airfoil having a leading edge, a trailing edge, a suction side, and a pressure side, wherein an airfoil cavity is formed within the airfoil, wherein the airfoil extends from an inner diameter to an outer diameter; and a divided baffle installed within the airfoil cavity, the divided baffle comprising: a baffle body having a first end and a second end, wherein the first end is located proximate the inner diameter and the second end is located proximate the outer diameter; at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities; at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities; and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities. ### Claim 15 (depends on 14) The gas turbine engine of claim 14, wherein the airfoil is a vane of a gas turbine engine. ### Claim 16 (depends on 14) The gas turbine engine of claim 14, wherein the airfoil cavity is a leading edge cavity of the airfoil. ### Claim 17 (depends on 14) The gas turbine engine of claim 14, wherein the airfoil extends between a first platform and a second platform. ### Claim 18 (depends on 17) The gas turbine engine of claim 17, wherein the first feed cavity is fluidly connected to the first platform and the second feed cavity is fluidly connected to the second platform. ### Claim 19 (depends on 18) The gas turbine engine of claim 18, wherein the cap at the first end prevents airflow from the second platform from entering the first feed cavity and the cap at the second end prevents airflow from the first platform from entering the second feed cavity. ### Claim 20 (depends on 14) The gas turbine engine of claim 14, wherein the first feed cavity is supplied with cooling air from an inner diameter of the airfoil and the second feed cavity is supplied with cooling air from an outer diameter of the airfoil such that airflow within the first feed cavity flows in a different direction than airflow within the second feed cavity.