FR3013252B1 - HYBRID MANUFACTURING METHOD OF A RECTIFIER BLADE FOR AERONAUTICAL GAS TURBINE ENGINE - Google Patents
HYBRID MANUFACTURING METHOD OF A RECTIFIER BLADE FOR AERONAUTICAL GAS TURBINE ENGINEInfo
- Publication number
- FR3013252B1 FR3013252B1 FR1361390A FR1361390A FR3013252B1 FR 3013252 B1 FR3013252 B1 FR 3013252B1 FR 1361390 A FR1361390 A FR 1361390A FR 1361390 A FR1361390 A FR 1361390A FR 3013252 B1 FR3013252 B1 FR 3013252B1
- Authority
- FR
- France
- Prior art keywords
- gas turbine
- turbine engine
- hybrid manufacturing
- rectifier blade
- aeronautical gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/467—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements during mould closing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Injection Moulding Of Plastics Or The Like (AREA)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1361390A FR3013252B1 (en) | 2013-11-20 | 2013-11-20 | HYBRID MANUFACTURING METHOD OF A RECTIFIER BLADE FOR AERONAUTICAL GAS TURBINE ENGINE |
PCT/FR2014/052850 WO2015075347A1 (en) | 2013-11-20 | 2014-11-07 | Method for hybrid manufacturing of a straightener vane for an aircraft gas-turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1361390A FR3013252B1 (en) | 2013-11-20 | 2013-11-20 | HYBRID MANUFACTURING METHOD OF A RECTIFIER BLADE FOR AERONAUTICAL GAS TURBINE ENGINE |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3013252A1 FR3013252A1 (en) | 2015-05-22 |
FR3013252B1 true FR3013252B1 (en) | 2015-12-18 |
Family
ID=49917154
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1361390A Active FR3013252B1 (en) | 2013-11-20 | 2013-11-20 | HYBRID MANUFACTURING METHOD OF A RECTIFIER BLADE FOR AERONAUTICAL GAS TURBINE ENGINE |
Country Status (2)
Country | Link |
---|---|
FR (1) | FR3013252B1 (en) |
WO (1) | WO2015075347A1 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3100741B1 (en) * | 2019-09-13 | 2021-09-10 | Safran | HOLLOW PART MANUFACTURING DEVICE |
US11352891B2 (en) | 2020-10-19 | 2022-06-07 | Pratt & Whitney Canada Corp. | Method for manufacturing a composite guide vane having a metallic leading edge |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1992020503A1 (en) * | 1991-05-24 | 1992-11-26 | Dow-United Technologies Composite Products, Inc. | Braided complex composite parts and methods of forming same |
IT1397058B1 (en) * | 2009-11-23 | 2012-12-28 | Nuovo Pignone Spa | CENTRIFUGAL IMPELLER MOLD, MOLD INSERTS AND METHOD TO BUILD A CENTRIFUGAL IMPELLER |
FR2953225B1 (en) * | 2009-11-30 | 2012-03-02 | Snecma | COMPONENT COMPRISING REINFORCING YARNS IN THE FORM OF CHAIN YARNS AND THREE-DIMENSIONED WOVEN FABRIC YARNS. |
-
2013
- 2013-11-20 FR FR1361390A patent/FR3013252B1/en active Active
-
2014
- 2014-11-07 WO PCT/FR2014/052850 patent/WO2015075347A1/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
WO2015075347A1 (en) | 2015-05-28 |
FR3013252A1 (en) | 2015-05-22 |
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