# US 2014/0154059 A1 · Turbine nozzle baffle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0154059 A1 - Document ID: US20140154059A1 - Status: Published application - Kind: A1 - Application number: 13/692,171 - Filed: 2012-12-03 - Published: 2014-06-05 - Earliest claimed: 2012-12-03 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Gordon F. Jewess - Web page: https://patentgrep.com/patent/US20140154059A1 ## CPC - F01D 25/12: Cooling - F01D 11/001: {for sealing space between stator blade and rotor} - Y10T 29/49323: Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract An embodiment of the present invention is a turbine nozzle baffle including an annular box structure. The turbine nozzle baffle includes a first diaphragm, a second diaphragm, and a static portion of a rotating seal that form a one-piece annular box structure. The first diaphragm extends from an inner diameter of the box structure to an outer diameter of the box structure to form a first axial side. The second diaphragm includes a first portion and a second portion. The first portion extends from the inner diameter to the outer diameter to form a second axial side. The second portion extends toward the first axial side to form the outer diameter. The second diaphragm connects to the first diaphragm at the outer diameter. The static portion of the rotating seal faces radially inward at the inner diameter between the first axial side and the second axial side. ## Claims ### Claim 1 A turbine nozzle baffle including an annular box structure, the baffle comprising: a first diaphragm extending from an inner diameter of the box structure to an outer diameter of the box structure to form a first axial side; a second diaphragm, a first portion of the second diaphragm extending from the inner diameter to the outer diameter to form a second axial side, the second axial side spaced apart from the first axial side in an axial direction; a second portion of the second diaphragm extending toward the first axial side to form the outer diameter; the second diaphragm connected to the first diaphragm at the outer diameter; and a static portion of a rotating seal facing radially inward at the inner diameter between the first axial side and the second axial side; wherein the first diaphragm, the second diaphragm, and the static portion of the rotating seal form a one-piece annular box structure. ### Claim 2 (depends on 1) The baffle of claim 1, wherein the first diaphragm includes a flange projecting radially outward from the outer diameter at the first axial side. ### Claim 3 (depends on 2) The baffle of claim 2, further including an interference fit ring connected to the outer diameter at the second axial side. ### Claim 4 (depends on 3) The baffle of claim 3, wherein the interference fit ring is a cast ring including a machined outside diameter surface. ### Claim 5 (depends on 3) The baffle of claim 3, wherein the static portion of the rotating seal connects to each of the first diaphragm and the second diaphragm at the inner diameter. ### Claim 6 (depends on 5) The baffle of claim 5, wherein the connections between the first diaphragm, and the second diaphragm; the static portion of the rotating seal, and each of the first diaphragm and the second diaphragm; and the interference fit ring, and the second diaphragm are brazed connections. ### Claim 7 (depends on 6) The baffle of claim 6, wherein the first diaphragm and the second diaphragm are formed from sheet metal. ### Claim 8 (depends on 7) The baffle of claim 7, wherein at least one of the sheet metal and the interference fit ring is made of a nickel-based alloy. ### Claim 9 (depends on 1) The baffle of claim 1, further including a plurality of lightening holes through the box structure at the outer diameter. ### Claim 10 An axial gas turbine engine comprising: a first turbine rotor; a second turbine rotor; a rotor shaft connecting the first turbine rotor to the second turbine rotor, the rotor shaft including a rotating portion of a rotating seal; a turbine nozzle between the first turbine rotor and the second turbine rotor; and a turbine nozzle baffle connected to an inner diameter of the turbine nozzle, the turbine nozzle baffle including a one-piece annular box structure. ### Claim 11 (depends on 10) The engine of claim 10, wherein the one-piece annular box structure comprises: a first diaphragm extending from an inner diameter of the baffle to an outer diameter of the baffle to form a first axial side; a second diaphragm, a first portion of the second diaphragm extending from the inner diameter of the baffle to the outer diameter of the baffle to form a second axial side, the second axial side spaced apart from the first axial side in an axial direction; a second portion of the second diaphragm extending toward the first axial side to form the outer diameter of the baffle; the second diaphragm connected to the first diaphragm at the outer diameter of the baffle; and a static portion of a rotating seal facing radially inward at the inner diameter of the baffle between the first axial side and the second axial side. ### Claim 12 (depends on 11) The engine of claim 11, wherein the static portion of the rotating seal and the rotating portion of the rotating seal cooperate to form a seal between a first cavity between the first turbine rotor and first axial side, and a second cavity between the second turbine rotor and the second axial side. ### Claim 13 (depends on 11) The engine of claim 11, wherein the first axial side is contoured to match a contour of the first turbine rotor and the second axial side is contoured to match a contour of the second turbine rotor. ### Claim 14 (depends on 11) The engine of claim 11, wherein the first diaphragm includes annular flange projecting radially outward from the outer diameter of the baffle at the first axial side. ### Claim 15 (depends on 14) The engine of claim 14, further including a retaining ring; wherein: the turbine nozzle includes: a flange recess extending circumferentially around the inner diameter of the turbine nozzle; and a retaining ring slot extending circumferentially around the inner diameter of the turbine nozzle adjacent to the flange slot; and the flange is disposed within the flange recess, and the retaining ring is disposed within the retaining ring slot to retain the flange within the flange recess to connect the flange to the inner diameter of the turbine nozzle. ### Claim 16 (depends on 14) The engine of claim 14, further including an interference fit ring connected to the outer diameter of the baffle at the second axial side. ### Claim 17 (depends on 16) The engine of claim 16, wherein the static portion of the rotating seal connects to each of the first diaphragm and the second diaphragm at the inner diameter of the baffle. ### Claim 18 A method of installing a turbine nozzle baffle in an inner diameter of a turbine nozzle comprises: altering the temperature of at least one of the turbine nozzle baffle and the turbine nozzle such that an outer diameter of an interference fit ring connected to an outer diameter of the turbine nozzle baffle fits within an inner diameter of the turbine nozzle; inserting the turbine nozzle baffle into the inner diameter of the turbine nozzle until a flange of the turbine nozzle baffle contacts a flange recess in the inner diameter of the turbine nozzle; securing the flange against the flange recess; and allowing the temperature of the turbine nozzle baffle and the turbine nozzle to equilibrate. ### Claim 19 (depends on 18) The method of claim 18, wherein securing the flange against the flange recess includes: compressing a retaining ring; inserting the compressed retaining ring into the inner diameter of the turbine nozzle until it contacts the flange of the turbine nozzle baffle; and releasing the compressed retaining ring such that it expands into a retaining ring slot in the inside diameter of the turbine nozzle, adjacent to the flange recess. ### Claim 20 (depends on 18) The method of claim 18, wherein securing the flange against the flange recess includes: aligning flange openings in the flange with recess openings at the flange recess; inserting fasteners into the aligned flange openings and recess openings; and securing the fasteners such that the flange is secured against the flange recess.