FR3130897B1 - AIRCRAFT TURBOMACHINE - Google Patents
AIRCRAFT TURBOMACHINE Download PDFInfo
- Publication number
- FR3130897B1 FR3130897B1 FR2113847A FR2113847A FR3130897B1 FR 3130897 B1 FR3130897 B1 FR 3130897B1 FR 2113847 A FR2113847 A FR 2113847A FR 2113847 A FR2113847 A FR 2113847A FR 3130897 B1 FR3130897 B1 FR 3130897B1
- Authority
- FR
- France
- Prior art keywords
- aircraft turbomachine
- annular
- straightener vanes
- rotor blade
- walls
- 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
- 238000011144 upstream manufacturing Methods 0.000 abstract 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
- 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
-
- 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
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
- F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
- F02C9/52—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by bleeding or by-passing the working fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Turbomachine (10) d’aéronef, comportant : - deux parois annulaires coaxiales (12, 14), - un aubage de rotor (30), - un séparateur annulaire (24) disposé en aval de l’aubage de rotor (30) et entre les deux parois (12, 14), et comportant en amont un bec annulaire (24a), - des aubes de redresseur fixes (42) reliées au bec (24a), et - des aubes de redresseur à calage variable (44) en aval des aubes de redresseur fixes (42). Figure pour l'abrégé : Figure 3aAircraft turbomachine (10), comprising: - two coaxial annular walls (12, 14), - a rotor blade (30), - an annular separator (24) arranged downstream of the rotor blade (30) and between the two walls (12, 14), and comprising upstream an annular nozzle (24a), - fixed straightener vanes (42) connected to the nozzle (24a), and - straightener vanes with variable pitch (44) in downstream of the fixed straightener vanes (42). Figure for abstract: Figure 3a
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2113847A FR3130897B1 (en) | 2021-12-17 | 2021-12-17 | AIRCRAFT TURBOMACHINE |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2113847A FR3130897B1 (en) | 2021-12-17 | 2021-12-17 | AIRCRAFT TURBOMACHINE |
FR2113847 | 2021-12-17 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3130897A1 FR3130897A1 (en) | 2023-06-23 |
FR3130897B1 true FR3130897B1 (en) | 2023-11-24 |
Family
ID=81448614
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR2113847A Active FR3130897B1 (en) | 2021-12-17 | 2021-12-17 | AIRCRAFT TURBOMACHINE |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3130897B1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11802525B2 (en) | 2022-01-07 | 2023-10-31 | General Electric Company | Outlet guide vane |
US11859515B2 (en) | 2022-03-04 | 2024-01-02 | General Electric Company | Gas turbine engines with improved guide vane configurations |
US11946378B2 (en) | 2022-04-13 | 2024-04-02 | General Electric Company | Transient control of a thermal transport bus |
US11927142B2 (en) | 2022-07-25 | 2024-03-12 | General Electric Company | Systems and methods for controlling fuel coke formation |
US12006880B2 (en) | 2022-09-12 | 2024-06-11 | General Electric Company | High bandwidth control of turbofan/turboprop thrust response using embedded electric machines |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3841091A (en) * | 1973-05-21 | 1974-10-15 | Gen Electric | Multi-mission tandem propulsion system |
US20110167784A1 (en) * | 2009-09-25 | 2011-07-14 | James Edward Johnson | Method of operating a convertible fan engine |
WO2015088833A1 (en) * | 2013-12-12 | 2015-06-18 | United Technologies Corporation | Systems and methods controlling fan pressure ratios |
US20190078536A1 (en) * | 2017-09-12 | 2019-03-14 | Rolls-Royce North American Technologies Inc. | Flow path splitter for turbofan gas turbine engines |
-
2021
- 2021-12-17 FR FR2113847A patent/FR3130897B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3130897A1 (en) | 2023-06-23 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20230623 |
|
PLFP | Fee payment |
Year of fee payment: 3 |