# US 11,306,659 B2 · Plug resistant effusion holes for gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,306,659 B2 - Document ID: US11306659B2 - Status: Granted - Kind: B2 - Application number: 16/423,579 - Filed: 2019-05-28 - Published: 2020-12-03 - Granted: 2022-04-19 - Earliest claimed: 2019-05-28 - Assignees: Honeywell International Inc. - Applicants: Honeywell International Inc. - Inventors: Rodolphe Dudebout; Nagaraja Rudrapatna - Web page: https://patentgrep.com/patent/US11306659B2 ## CPC - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - 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 5/186: {Film cooling (F01D5/187 takes precedence)} - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/06: Arrangement of apertures along the flame tube - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor - F05D 2260/201: by impingement of a fluid - F05D 2260/202: by film cooling - F05D 2260/2214: by increasing the heat transfer surface - F05D 2260/607: Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles - F23R 2900/00004: Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits - F23R 2900/03041: Effusion cooled combustion chamber walls or domes - F23R 2900/03042: Film cooled combustion chamber walls or domes - F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - 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 effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet. ## Claims ### Claim 1 An effusion cooling hole for a component associated with a gas turbine engine, the component including a wall having a cold, first surface opposite a hot, second surface and a thickness defined between the first surface and the second surface, the effusion cooling hole extending along a longitudinal axis, the effusion cooling hole comprising: an inlet section spaced apart from the first surface, the inlet section including a face orientated transverse to the first surface and defining an inlet through the face that is symmetric to the longitudinal axis, the face extends about a perimeter of the inlet, the inlet having a first diameter, the face having a diameter that is greater than the first diameter, and at least a portion of the face is in contact with the first surface at a perimeter of the face; an outlet at the second surface and downstream from the inlet section, the outlet configured to form a film of a cooling fluid on the second surface, the outlet having an elliptical opening with a third major diameter that is different than the diameter; a diverging section downstream from the inlet section and upstream from the outlet, the diverging section is defined substantially external to the thickness, the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section and the second diameter is larger than the first diameter; and an intermediate section that fluidly connects the diverging section to the outlet, the intermediate section defined at least through the thickness and having the second diameter from the diverging section to the outlet. ### Claim 2 (depends on 1) The effusion cooling hole of claim 1, wherein the face is planar, the face extends along a first axis that is transverse to the longitudinal axis and the first surface, and the face symmetric to the longitudinal axis. ### Claim 3 (depends on 2) The effusion cooling hole of claim 2, wherein the first axis is at a first angle relative to the first surface, and the first angle is between 10 degrees and 25 degrees. ### Claim 4 (depends on 2) The effusion cooling hole of claim 2, wherein the longitudinal axis is transverse to a first normal of the first surface and is transverse to a second normal of the second surface such that the inlet of the effusion cooling hole is offset from the outlet of the effusion cooling hole and the effusion cooling hole is angled through the wall of the component. ### Claim 5 (depends on 1) The effusion cooling hole of claim 1, wherein the diverging section is defined wholly external to the thickness and a portion of the intermediate section is defined external to the thickness. ### Claim 6 (depends on 1) The effusion cooling hole of claim 1, wherein the diverging section is defined such that greater than 80% of the diverging section is external to the thickness. ### Claim 7 (depends on 1) The effusion cooling hole of claim 1, wherein the third major diameter is greater than the second diameter and the first diameter. ### Claim 8 (depends on 1) The effusion cooling hole of claim 1, wherein the inlet is defined through the face to define a corner about the perimeter of the inlet between a wall of the diverging section and the face, the corner having a first angle that is between 45 and 90 degrees. ### Claim 9 (depends on 1) The effusion cooling hole of claim 1, further comprising a guide flange that surrounds and extends outwardly from the face. ### Claim 10 (depends on 1) The effusion cooling hole of claim 1, wherein the inlet includes a taper that extends from the face to the first diameter. ### Claim 11 (depends on 1) The effusion cooling hole of claim 1, wherein the face is planar, and is configured such that cooling fluid enters the inlet normal to the face. ### Claim 12 (depends on 1) The effusion cooling hole of claim 1, wherein the component is at least one of a turbine blade associated with the gas turbine engine, an inner liner of a combustor associated with the gas turbine engine and an outer liner of a combustor associated with the gas turbine engine. ### Claim 13 (depends on 1) The effusion cooling hole of claim 1, wherein the diverging section has a first length, the intermediate section has a second length, the second length is greater than the first length and the intermediate section is symmetric to the longitudinal axis. ### Claim 14 (depends on 1) The effusion cooling hole of claim 1, wherein the diverging section forms a vena contracta that is configured to inhibit the accumulation of fine particles within the effusion cooling hole. ### Claim 15 An effusion cooling hole for a component associated with a gas turbine engine, the component including a wall having a cold, first surface opposite a hot, second surface and a thickness defined between the first surface and the second surface, the effusion cooling hole extending along a longitudinal axis and angled relative to the second surface, the effusion cooling hole comprising: an inlet section spaced apart from the first surface, the inlet section including a planar face orientated transverse to the first surface and defining an inlet through the planar face that is symmetric to the longitudinal axis, the inlet having a first diameter, the planar face having a diameter that is greater than the first diameter, and at least a portion of the planar face is in contact with the first surface at a perimeter of the planar face; an outlet at the second surface and downstream from the inlet section, the outlet configured to form a film of a cooling fluid on the second surface, the outlet having an elliptical opening with a third major diameter that is different than the diameter; a diverging section downstream from the inlet section and upstream from the outlet, the diverging section is defined substantially external to the thickness, the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section, the second diameter is larger than the first diameter and the diverging section has a first length; and an intermediate section that extends from the diverging section to the outlet, the intermediate section symmetric to the longitudinal axis, the intermediate section defined at least through the thickness, the intermediate section has the second diameter from the diverging section to the outlet and the intermediate section has a second length that is greater than the first length of the diverging section. ### Claim 16 (depends on 15) The effusion cooling hole of claim 15, wherein the diverging section is defined wholly external to the thickness and a portion of the intermediate section is defined external to the thickness. ### Claim 17 (depends on 15) The effusion cooling hole of claim 15, wherein the diverging section is defined such that greater than 80% of the diverging section is external to the thickness. ### Claim 18 (depends on 15) The effusion cooling hole of claim 15, wherein the third major diameter is greater than the second diameter and the first diameter. ### Claim 19 (depends on 15) The effusion cooling hole of claim 15, wherein the planar face extends along a first axis transverse to the longitudinal axis and the first surface, the first axis is at a first angle relative to the first surface, the first angle is between 10 degrees and 25 degrees, and the planar face symmetric to the longitudinal axis. ### Claim 20 An effusion cooling hole for a component associated with a gas turbine engine, the component including a wall having a cold, first surface opposite a hot, second surface and a thickness defined between the first surface and the second surface, the effusion cooling hole extending along a longitudinal axis and angled relative to the second surface, the effusion cooling hole comprising: an inlet section spaced apart from the first surface, the inlet section including a planar face orientated along a first axis transverse to the first surface and the longitudinal axis, the first axis is at a first angle relative to the first surface, the first angle between 10 degrees and 25 degrees, the inlet section defining an inlet through the planar face that is symmetric to the longitudinal axis, the planar face surrounding the inlet and the inlet having a first diameter, the planar face having a diameter that is greater than the first diameter, and at least a portion of the planar face is in contact with the first surface at a perimeter of the planar face; an outlet at the second surface and downstream from the inlet section, the outlet configured to form a film of a cooling fluid on the second surface, the outlet having an elliptical opening with a third major diameter that is different than the diameter; a diverging section downstream from the inlet section and upstream from the outlet and the diverging section is defined wholly external to the thickness, the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section, the second diameter is larger than the first diameter, smaller than the third diameter and smaller than the diameter, and the diverging section has a first length; and an intermediate section that fluidly connects the diverging section to the outlet, the intermediate section defined at least through the thickness, the intermediate section having the second diameter from the diverging section to the outlet and the intermediate section has a second length that is greater than the first length of the diverging section.