# US 4,396,349 A · Turbine blade, more particularly turbine nozzle vane, for 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 4,396,349 A - Document ID: US4396349A - Status: Granted - Kind: A - Application number: 06/357,629 - Filed: 1982-03-12 - Granted: 1983-08-02 - Earliest claimed: 1981-03-16 - Assignees: Motoren- und Turbinen-Union Munchen GmbH - Inventors: Alfred Hueber - Web page: https://patentgrep.com/patent/US4396349A ## CPC - F01D 5/284: {Selection of ceramic materials} - 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) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A turbine blade, more particularly a turbine nozzle vane, for a gas turbine engine, consisting of a structural metallic core enveloped at a distance by a ceramic blade jacket. Through provision a primarily highly heat-resistant, ceramic metal compound structure of the blade, the blade jacket is compressively prestressed spanwise between the blade shrouds in the inoperative condition of the turbine and where said compressive prestressing of the blade jacket, produced during assembly and which exists in the inoperative condition, is at least maintained during the operation condition by selecting for the metallic core of the blade, a material of average coefficient of thermal expansion and for the metallic inner and outer shrouds of the blade, and for the inner and outer metallic, sleeve-like components producing the axial prestress, materials of higher coefficients of thermal expansion, and for the highly thermally stressed ceramic blade jacket, a material of average coefficient of thermal expansion. ## Claims ### Claim 1 In a turbine blade, particularly a turbine nozzle vane, for gas turbine engines, including a structurally supportive metallic core, a ceramic blade jacket encasing said core so as to form a space therebetween, at least one spanwise-oriented cooling air duct in said space, and where inner and outer blade shroud means for suspending the turbine vane from structural inner and outer casing components for centered positioning and for limited radial and axial thermoelastic flexibility; the improvement comprising: (a) said blade jacket being inserted into recesses in the inner and outer blade shroud means and being subjected to compressive prestressing in the spanwise direction between the shroud means; (b) first and second sleeve-like components being acted upon by concurrent forces to produce said compressive stress and being welded to the metallic core, each said component engaging, with its end pointing away from the weld and facing the core, in a corresponding recess in, respectively, the inner and outer shroud means; (c) a spanwise oriented heat shield being arranged in the space between the blade core and the jacket; a cooling air duct being enclosed between the shield and the blade core; (d) said structural arrangement of the blade maintaining the compressive prestressing of the blade jacket produced during assembly in the operating condition, said metallic blade core being a material having a moderate coefficient of thermal expansion is selected, said metallic inner and outer shroud means and the inner and outer metallic sleeve-like components being formed of materials having a higher coefficient of thermal expansion; and the highly thermally stressed or thermally resistant ceramic blade jacket being formed of a material of average coeffecient of thermal expansion. ### Claim 2 (depends on 1) Turbine blade as claimed in claim 1, wherein the heat shield includes a thermally insulating layer on the side facing towards the blade jacket. ### Claim 3 (depends on 2) Turbine blade as claimed in claim 2, said insulating layer comprising ZrO.sub.2. ### Claim 4 (depends on 1, 2) Turbine blade as claimed in claim 1 or 2, wherein the contacting surfaces formed by the recesses of the inner and outer shrouds for the ceramic blade jacket are provided with ductile, thermally insulating shim means. ### Claim 5 (depends on 4) Turbine blade as claimed in claim 4, wherein the shim has a sheet form. ### Claim 6 (depends on 1) Turbine blade as claimed in claim 1, wherein the heat shield includes button-like protuberances at least partially abutting the blade core or the blade jacket. ### Claim 7 (depends on 1) Turbine blade as claimed in claim 1, wherein the inner shroud is positioned on an inner nozzle vane carrier through a centering connection on one side thereof and a tongue-and-groove type, radially flexible connection on the other side thereof. ### Claim 8 (depends on 1) Turbine blade as claimed in claim 1, wherein the blade core (2) extends into proximity with the annular circumferential wall of the vane carrier so as to define, in conjunction with the inner sleeve-like component and wall portions of the inner blade shroud means, an annulus supplied with cooling air, said annulus communicating with a duct formed between the sleeve-like component and the blade core, the lower end of the heat shield projecting into said duct so that said duct directly communicates with the blade cooling duct between the core and the heat shield, and a sheet-like metallic seal being provided so as to bridge the space between the heat shield and the inner blade shroud. ### Claim 9 (depends on 1) Turbine blade as claimed in claim 1, wherein the heat shield is attached to a retaining plate in the recess between the outer shroud means and the end of the outer sleeve-like component abutting thereagainst. ### Claim 10 (depends on 1) Turbine blade as claimed in claim 1, said metallic blade core including the outer sleeve-like component being arranged above the ceramic blade jacket in an annulus defined by the casing components and by portions of the outer shroud means, said annulus communicating through apertures in the outer wall of the outer sleeve-like component with a duct formed between the sleeve-like component and the blade core, said duct communicating with the blade cooling duct formed between the core and the heat shield. ### Claim 11 (depends on 1) Turbine blade as claimed in claim 1, wherein the outer shroud means is suspended from outer casing components through axially extending tongue-and-groove connections, one said connection being axially flexible.