FR3066779B1 - Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure - Google Patents
Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure Download PDFInfo
- Publication number
- FR3066779B1 FR3066779B1 FR1754663A FR1754663A FR3066779B1 FR 3066779 B1 FR3066779 B1 FR 3066779B1 FR 1754663 A FR1754663 A FR 1754663A FR 1754663 A FR1754663 A FR 1754663A FR 3066779 B1 FR3066779 B1 FR 3066779B1
- Authority
- FR
- France
- Prior art keywords
- blade
- turbomachine
- turbomachine blade
- measuring parameters
- aerodynamic flow
- 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
- 238000005259 measurement Methods 0.000 title 1
Classifications
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- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/02—Arrangement of sensing elements
- F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
-
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/83—Testing, e.g. methods, components or tools therefor
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
L'invention concerne un dispositif (1) de mesure de paramètres d'un flux aérodynamique d'une turbomachine, le dispositif (1) comprenant des moyens de relevé d'informations (2) relatives aux paramètres du flux, et un corps (3) comprenant lesdits moyens de relevé d'informations (2). Selon l'invention, le corps (3) présente une partie (4) allongée suivant une direction longitudinale (L) configurée pour former le bord d'attaque d'une pale (66) de la turbomachine et une première portion latérale (15, 16) prolongeant latéralement la partie (4) suivant une direction axiale (A), les moyens de relevé d'informations (2) étant agencés en saillie depuis le bord d'attaque de la partie (4) et la partie (4) comprenant des canaux internes (9) d'acheminement des informations en communication chacun au moins avec un moyen de relevé d'informations (2), la première portion latérale (15, 16) présentant une première surface (18, 20) configurée de manière à épouser au moins en partie une deuxième surface (19) d'une paroi intrados ou extrados d'une pale de turbomachine.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1754663A FR3066779B1 (fr) | 2017-05-26 | 2017-05-26 | Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure |
US15/988,982 US10683771B2 (en) | 2017-05-26 | 2018-05-24 | Measuring device for measuring aerodynamic flow parameters of a turbomachine vane, vane and part of turbomachine equipped with said measuring device |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1754663 | 2017-05-26 | ||
FR1754663A FR3066779B1 (fr) | 2017-05-26 | 2017-05-26 | Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3066779A1 FR3066779A1 (fr) | 2018-11-30 |
FR3066779B1 true FR3066779B1 (fr) | 2020-04-03 |
Family
ID=59409529
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR1754663A Active FR3066779B1 (fr) | 2017-05-26 | 2017-05-26 | Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure |
Country Status (2)
Country | Link |
---|---|
US (1) | US10683771B2 (fr) |
FR (1) | FR3066779B1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3044412B1 (fr) * | 2015-11-30 | 2018-11-09 | Safran Aircraft Engines | Veine instrumentee de turbomachine |
FR3090102A1 (fr) | 2018-12-17 | 2020-06-19 | Airbus Operations | Outil de mesure de pression comportant un fourreau pour sa mise en place dans une veine d’un moteur d’aeronef |
US11692455B1 (en) * | 2022-09-19 | 2023-07-04 | Pratt & Whitney Canada Corp. | Passively orientable pressure probe |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB759268A (en) * | 1953-07-14 | 1956-10-17 | Power Jets Res & Dev Ltd | Method of mounting instruments in turbines and compressors |
US4433584A (en) * | 1981-11-27 | 1984-02-28 | United Technologies Corp. | Total pressure probe |
US4605315A (en) * | 1984-12-13 | 1986-08-12 | United Technologies Corporation | Temperature probe for rotating machinery |
US4765751A (en) * | 1987-06-29 | 1988-08-23 | United Technologies Corporation | Temperature and pressure probe |
GB0510440D0 (en) * | 2005-05-21 | 2005-06-29 | Rolls Royce Plc | An instrumentation rake |
US7527471B2 (en) * | 2006-07-31 | 2009-05-05 | General Electric Company | Stator vane and gas turbine engine assembly including same |
US9297720B2 (en) * | 2012-12-21 | 2016-03-29 | United Technologies Corporation | Gas turbine engine vane embedded beam interrupt optical tip-timing probe system |
US20140182292A1 (en) * | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Integral instrumentation in additively manufactured components of gas turbine engines |
FR3012169B1 (fr) * | 2013-10-21 | 2018-01-12 | Safran Aircraft Engines | Pale instrumentee |
WO2015119792A1 (fr) * | 2014-02-05 | 2015-08-13 | United Technologies Corporation | Instrument intégré dans des composants de turbines à gaz fabriqués de manière additive |
FR3017459B1 (fr) * | 2014-02-07 | 2017-07-21 | Snecma | Aube instrumentee a tube rapporte dans une rainure |
US9856743B2 (en) * | 2014-05-28 | 2018-01-02 | Safran Aircraft Engines | Instrumented flow passage of a turbine engine |
GB201507281D0 (en) * | 2015-04-29 | 2015-06-10 | Composite Technology & Applic Ltd | Methods and systems for bonding |
GB2541356A (en) * | 2015-06-08 | 2017-02-22 | Meggitt (Uk) Ltd | Moving-vane angle of attack probe |
FR3043775B1 (fr) * | 2015-11-12 | 2017-11-10 | Snecma | Dispositif de mesure de grandeurs aerodynamiques destine a etre place dans une veine d'ecoulement d'une turbomachine |
WO2018156335A2 (fr) * | 2017-02-03 | 2018-08-30 | Aurora Flight Sciences Corporation | Système et procédé de détection de débit d'air distribuée |
-
2017
- 2017-05-26 FR FR1754663A patent/FR3066779B1/fr active Active
-
2018
- 2018-05-24 US US15/988,982 patent/US10683771B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US10683771B2 (en) | 2020-06-16 |
US20180340444A1 (en) | 2018-11-29 |
FR3066779A1 (fr) | 2018-11-30 |
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