FR3117153B1 - Method for characterizing the aerodynamic performance of stator blades - Google Patents
Method for characterizing the aerodynamic performance of stator blades Download PDFInfo
- Publication number
- FR3117153B1 FR3117153B1 FR2012648A FR2012648A FR3117153B1 FR 3117153 B1 FR3117153 B1 FR 3117153B1 FR 2012648 A FR2012648 A FR 2012648A FR 2012648 A FR2012648 A FR 2012648A FR 3117153 B1 FR3117153 B1 FR 3117153B1
- Authority
- FR
- France
- Prior art keywords
- aerodynamic performance
- blades
- characterizing
- propulsion propeller
- given
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
La présente invention concerne un procédé de caractérisation des performances aérodynamiques d’aubes de stator (6) agencées en aval d’aubes d’une hélice de propulsion (4) d’un système propulsif (1) d’axe longitudinal (2), les aubes de stator recevant un écoulement d’air ayant une vitesse V12, qui est la vitesse de flux d'air sortant des aubes de l'hélice de propulsion, comportant une composante longitudinale Viz et une composante tangentielle associées à une vitesse de giration générée par l’hélice de propulsion, le procédé comprenant les étapes :a) calculer, pour un nombre de Mach donné à une vitesse de vol V0 donnée, des performances aérodynamiques des aubes de l’hélice de propulsion (4) comprenant un ratio d’avancement J1, un angle de calage ;b) calculer, pour un nombre de Mach donné à une vitesse de vol V0 donnée, un angle d’écoulement fonction du ratio d’avancement J1 pour une pluralité d’angle de calage . Figure à publier avec l’abrégé : Figure 7The present invention relates to a method for characterizing the aerodynamic performance of stator vanes (6) arranged downstream of the vanes of a propulsion propeller (4) of a propulsion system (1) of longitudinal axis (2), the stator blades receiving an air flow having a speed V12, which is the air flow speed exiting the blades of the propulsion propeller, comprising a longitudinal component Viz and a tangential component associated with a generated rate of gyration by the propulsion propeller, the method comprising the steps: a) calculating, for a given Mach number at a given flight speed V0, aerodynamic performance of the blades of the propulsion propeller (4) comprising a ratio of advancement J1, a pitch angle; b) calculating, for a given Mach number at a given flight speed V0, a flow angle as a function of the advancement ratio J1 for a plurality of pitch angles. Figure to be published with abstract: Figure 7
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2012648A FR3117153B1 (en) | 2020-12-03 | 2020-12-03 | Method for characterizing the aerodynamic performance of stator blades |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2012648 | 2020-12-03 | ||
FR2012648A FR3117153B1 (en) | 2020-12-03 | 2020-12-03 | Method for characterizing the aerodynamic performance of stator blades |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3117153A1 FR3117153A1 (en) | 2022-06-10 |
FR3117153B1 true FR3117153B1 (en) | 2022-11-18 |
Family
ID=74592170
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR2012648A Active FR3117153B1 (en) | 2020-12-03 | 2020-12-03 | Method for characterizing the aerodynamic performance of stator blades |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3117153B1 (en) |
-
2020
- 2020-12-03 FR FR2012648A patent/FR3117153B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3117153A1 (en) | 2022-06-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3692425A (en) | Compressor for handling gases at velocities exceeding a sonic value | |
US20040197187A1 (en) | Apparatus and method for enhancing lift produced by an airfoil | |
US9004850B2 (en) | Twisted variable inlet guide vane | |
JP2016114055A (en) | Turbine engine and method of assembling the same | |
RU2599694C2 (en) | Aircraft engine assembly and aircraft engine | |
EP2971550B1 (en) | Fan airfoil shrouds with area ruling in the shrouds | |
US20170369153A1 (en) | Turbomachine with multi-diameter propeller | |
KR102403377B1 (en) | Exhaust diffuser | |
US11131205B2 (en) | Inter-turbine ducts with flow control mechanisms | |
Goltz et al. | Stall inception phenomena in a single-stage axial-flow pump | |
GB2606681A (en) | Profiled structure for an aircraft or turbomachine for an aircraft | |
FR3117153B1 (en) | Method for characterizing the aerodynamic performance of stator blades | |
EP3098383B1 (en) | Compressor airfoil with compound leading edge profile | |
CA3052525A1 (en) | Compressor diffuser with plasma actuators | |
CN111742116B (en) | Turbine engine with a saw tooth profile split slat | |
NL8303937A (en) | DIFFUSER, ESPECIALLY SUITABLE FOR HIGH POWER GAS TURBINES. | |
JP6866187B2 (en) | Turbine nozzle and radial turbine equipped with it | |
US10746184B2 (en) | Turbine engine compressor with a turbulence sensor | |
FR3109140B1 (en) | System for determining the angular setting of an annular row of stator vanes | |
OTSUKA et al. | Numerical analysis of flow in radial turbine (Effects of nozzle vane angle on internal flow) | |
RU2780265C2 (en) | Turbomachine with slat for flow separation, having gear profile | |
EP2677123B2 (en) | Diffuser for turbomachines | |
RU2452876C1 (en) | Radial-flow compressor stage | |
Schwind et al. | A Look at Compressor Impeller Technologies for Turbochargers Focusing on Surge Mitigation | |
RU2538748C1 (en) | Water-jet propeller |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20220610 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |