# US 12,180,860 B2 · Guide vanes assembly with position-maintaining device > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,180,860 B2 - Document ID: US12180860B2 - Status: Granted - Kind: B2 - Application number: 18/546,169 - Filed: 2022-02-08 - Published: 2024-04-25 - Granted: 2024-12-31 - Earliest claimed: 2021-02-12 - Assignees: Safran Aircraft Engines; Safran Ceramics - Applicants: Safran Aircraft Engines; Safran Ceramics - Inventors: Sébastien Serge Francis Congratel; Aurélien Gaillard; Matthieu Arnaud Gimat; Clément Jarrossay; David René Pierre Le Cair - Web page: https://patentgrep.com/patent/US12180860B2 ## CPC - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/246: {Fastening of diaphragms or stator-rings} - F05D 2230/642: using maintaining alignment while permitting differential dilatation - F05D 2250/71: curved - F05D 2250/75: given by its similarity to a letter, e.g. T-shaped - F05D 2260/38: by a spring, i.e. spring loaded or biased towards a certain position - F05D 2300/6033: Ceramic matrix composites [CMC] - 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 A turbine engine nozzle extending about an axis and including a vane assembly mounted between an outer shroud and an inner shroud; and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress on the vane assembly towards the outer shroud. The contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device. ## Claims ### Claim 1 A turbine engine nozzle extending about an axis and comprising: a vane assembly mounted between an outer shroud and an inner shroud, and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress onto the vane assembly oriented towards the outer shroud, wherein contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device, and wherein the position retaining device comprises two curved metal sheets having common ends. ### Claim 2 (depends on 1) The nozzle according to claim 1, wherein one of the two metal sheets is interlocked in the other of the two metal sheets. ### Claim 3 (depends on 1) The nozzle according to claim 1, wherein prestressing is performed for a compression corresponding to a displacement of between 0.2 mm and 1 mm between a state of rest and the elastically prestressed state. ### Claim 4 (depends on 1) The nozzle according to claim 1, wherein prestressing is obtained by mounting the vane assembly on the position retaining device between the outer shroud and the inner shroud. ### Claim 5 (depends on 4) The nozzle according to claim 4, wherein the vane assembly comprises at least one hollow vane to allow the passing of a radial strut securing the inner shroud to the outer shroud. ### Claim 6 (depends on 5) The nozzle according to claim 5, comprising at least two position retaining devices circumferentially connected and each arranged against at least one vane. ### Claim 7 (depends on 4) The nozzle according to claim 4, wherein the inner shroud has a clamping protrusion configured to limit displacement of the position retaining device in a circumferential direction of the nozzle. ### Claim 8 (depends on 1) The nozzle according to claim 1, wherein the vane assembly is in ceramic matrix composite. ### Claim 9 (depends on 1) A turbine engine comprising the nozzle according to claim 1. ### Claim 10 A turbine engine nozzle extending about an axis and comprising: a vane assembly mounted between an outer shroud and an inner shroud, and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress onto the vane assembly oriented towards the outer shroud, wherein contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device, and wherein prestressing is performed for a compression corresponding to a displacement of between 0.2 mm and 1 mm between a state of rest and the elastically prestressed state. ### Claim 11 (depends on 10) A turbine engine comprising the nozzle according to claim 10. ### Claim 12 A turbine engine nozzle extending about an axis and comprising: a vane assembly mounted between an outer shroud and an inner shroud, and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress onto the vane assembly oriented towards the outer shroud, wherein contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device, wherein the vane assembly comprises at least one hollow vane to allow the passing of a radial strut securing the inner shroud to the outer shroud, and wherein the nozzle further comprises at least two position retaining devices circumferentially connected and each arranged against at least one vane. ### Claim 13 (depends on 12) A turbine engine comprising the nozzle according to claim 12. ### Claim 14 A turbine engine nozzle extending about an axis and comprising: a vane assembly mounted between an outer shroud and an inner shroud, and a position retaining device configured to be placed in an elastically prestressed state between the inner shroud and an inner platform of the vane assembly to apply a stress onto the vane assembly oriented towards the outer shroud, wherein contact between the inner shroud and the inner platform is obtained by one same surface of the position retaining device, wherein the position retaining device comprises at least one curved metal sheet presenting a C-shape, wherein a first end of the at least one curved metal sheet corresponds to a first contact zone between the position retaining device and the inner platform of the vane assembly when the position retaining device is mounted in the nozzle, and wherein a second end of the at least one curved metal sheet corresponds to a second contact zone between the position retaining device and the inner shroud when the position retaining device is mounted in the nozzle.