# US 10,371,054 B2 · Cooling-air supply device for a gas turbine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,371,054 B2 - Document ID: US10371054B2 - Status: Granted - Kind: B2 - Application number: 14/972,767 - Filed: 2015-12-17 - Published: 2016-06-23 - Granted: 2019-08-06 - Earliest claimed: 2014-12-17 - Assignees: MTU Aero Engines AG - Applicants: MTU Aero Engines AG - Inventors: Stefan Sasse; Erwin Bayer - Web page: https://patentgrep.com/patent/US10371054B2 ## CPC - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) - F01D 5/082: {on the side of the rotor disc} - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F05D 2220/3213: an intermediate stage of the turbine - F05D 2230/54: by sheet metal manufacturing - F05D 2240/35: Combustors or associated equipment - F05D 2240/61: Hollow - F05D 2260/14: Preswirling - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/201: by impingement of a fluid - F05D 2300/6033: Ceramic matrix composites [CMC] - F05D 2300/702: Reinforcement - 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) - 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 A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine. In the axial direction, the respective axial bounding wall having the cooling-air outlet orifices has a layer-type structure; the cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer. ## Claims ### Claim 1 A cooling-air supply device for a gas turbine comprising: a cooling air chamber disposed about a turbine shaft of the gas turbine; at least one cooling-air inlet opening and a plurality of cooling-air outlet orifices; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall joining the first and second axial bounding walls, together, forming the cooling air chamber; at least one of the first and second axial bounding walls having the plurality of cooling-air outlet orifices circumferentially distributed about the turbine shaft and adapted to allow cooling air to be discharged from the plurality of cooling-air outlet orifices in a direction of rotation of the gas turbine, wherein, in the axial direction, the at least one of the first and second axial bounding walls having the plurality of cooling-air outlet orifices having a layer structure; the plurality of cooling-air outlet orifices being formed by deformation of at least one first cooling air chamber-side layer and by deformation of at least one second, turbine-side layer. ### Claim 2 (depends on 1) The cooling-air supply device as recited in claim 1 wherein the plurality of cooling-air outlet orifices are formed by deformation of the at least one first cooling-air side layer and the at least one second, turbine-side layer in axially mutually opposing regions. ### Claim 3 (depends on 2) The cooling-air supply device as recited in claim 2 wherein the deformations are configured to complement one another. ### Claim 4 (depends on 2) The cooling-air supply device as recited in claim 2 wherein the deformations are designed in a way that forms cooling air channels by placing the at least one first cooling-air side layer and the at least one second, turbine-side layer against each other to establish a fluid communication between the cooling air chamber and an ambient environment of the cooling-air supply device. ### Claim 5 (depends on 1) The cooling-air supply device as recited in claim 1 wherein the deformations are in a bead form, each being angular or curved. ### Claim 6 (depends on 5) The cooling-air supply device as recited in claim 5 wherein the deformations each have an arcuate geometry in cross section. ### Claim 7 (depends on 5) The cooling-air supply device as recited in claim 5 wherein the bead deformations have a top chord extending obliquely relative to a respective one of the at least one first cooling-air side layer or the at least one second, turbine-side layer. ### Claim 8 (depends on 5) The cooling-air supply device as recited in claim 5 wherein the bead deformations have an unattached end separated from a respective one of the at least one first cooling-air side layer or the at least one second, turbine-side layer. ### Claim 9 (depends on 5) The cooling-air supply device as recited in claim 5 wherein bead deformations of the at least one first cooling-air side layer and the at least one second, turbine-side layer, the at least one first cooling-air side layer and the at least one second, turbine-side configured to mutually oppose one another, delimit an obliquely extending cooling air channel, having a cooling chamber-side opening and having a turbine-side opening formed by at least one unattached end of the bead deformations. ### Claim 10 (depends on 1) The cooling-air supply device as recited in claim 1 wherein the first or second axial bounding wall having the plurality of cooling-air outlet orifices has at least two mutually joined metal sheets, each of the metal sheets forming a layer. ### Claim 11 (depends on 1) The cooling-air supply device as recited in claim 1 wherein the first or second axial bounding wall having the plurality of cooling-air outlet orifices is formed from at least two joined together layers of ceramic fiber composite materials in which corresponding deformations are configured to form the plurality of cooling-air outlet orifices. ### Claim 12 (depends on 1) A gas turbine comprising: a compressor device; a combustion chamber; and a turbine, wherein, in the area of the turbine, the gas turbine has a cooling-air supply device as recited in claim 1. ### Claim 13 (depends on 12) The gas turbine as recited in claim 12 wherein the turbine has a high-pressure turbine and a low-pressure turbine, the cooling-air supply device being part of an intermediate turbine housing of the gas turbine. ### Claim 14 (depends on 13) The gas turbine as recited in claim 13 wherein the first or second axial bounding wall of the cooling-air supply device having the plurality of cooling-air outlet orifices is disposed toward the high-pressure turbine or toward the low-pressure turbine. ### Claim 15 (depends on 12) An aircraft gas turbine comprising the gas turbine as recited in claim 12.