WO2024242589A2 - Forme de pales de soufflante - Google Patents
Forme de pales de soufflante Download PDFInfo
- Publication number
- WO2024242589A2 WO2024242589A2 PCT/RU2024/000234 RU2024000234W WO2024242589A2 WO 2024242589 A2 WO2024242589 A2 WO 2024242589A2 RU 2024000234 W RU2024000234 W RU 2024000234W WO 2024242589 A2 WO2024242589 A2 WO 2024242589A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- root
- section
- profile
- chord
- 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.)
- Ceased
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
Definitions
- the invention relates to fans of gas turbine engines, in particular to fans of turbojet fan engines.
- the most effective application is in low-power turbojet fan engines with a thrust of 1000 to 5000 N.
- a gas turbine engine usually contains a fan that forces air flow into the engine compressor; in a dual-circuit engine, the fan also serves as a source of additional thrust by forcing air flow into the outer contour of the engine.
- the fan wheel consists of a base on which a plurality of blades are placed, forming a non-separable structure with the base, or blades that are fixed to the base with the possibility of removal without destroying the structure and even turning around its axis to change the engine thrust. Further development of the technical characteristics of turbofan engines leads to the need to use fans with blades or vanes operating at supersonic speeds, while having high efficiency and acceptable strength.
- the blade design is known (invention certificate RU No. 2255248 C2).
- the blade includes a chord convexity on the leading edge between the root and the tip and has a reverse aerodynamic sweep at the tip.
- the blade geometry is difficult to manufacture
- the split design of the fan makes it expensive and significantly difficult to use in low-power engines
- installing the blade in the confuser relative to the outer casing of the engine reduces the efficiency of the fan as a whole
- the rounded leading edge limits the maximum blade rotation speeds, creating high flow resistance at Mach speeds above 1.
- a design of a turbojet engine fan blade is known (Invention Certificate RU No. 2486346C2).
- a turbojet engine fan blade with a double flow comprising an internal aerodynamic part and an external aerodynamic part, combined in the radial direction and separated by a platform, wherein the internal aerodynamic part comprises one aerodynamic profile, and the external aerodynamic part comprises at least two aerodynamic profiles, wherein the attack ribs of said aerodynamic profiles of said aerodynamic part of the blade are axially aligned in a row.
- a reduction in the number of fan blades is achieved while maintaining satisfactory quality due to maintaining an increased relative pitch of the internal aerodynamic part of the fan blade.
- a known axial fan blade (Invention Certificate RU No. 2516739 C1) is accepted as the closest analogue based on a number of features.
- the blade comprises a convex approach edge, a concave trailing edge, a root portion and an upper edge.
- the radius of curvature of the concave trailing edge is made equal to the radius of curvature of the blade centerline, and the radius of curvature of the convex approach edge is selected based on ensuring the required blade thickness in the average cross-section along its length.
- the performance, pressure and efficiency of the fan are increased while maintaining the required strength and rigidity of the blade during operation.
- the disadvantages of this solution are: operation at low, subsonic peripheral speeds of the blade, the geometry of the blade is designed for relatively low axial air flow speeds, the relationship between the outer diameter of the fan wheel and the inner diameter to which this solution is applicable is not taken into account.
- the set objective is achieved by: using simple geometric shapes when constructing the blade profile, optimizing the blade inclination angles to the air flow and optimizing the number of blades on the fan impeller for maximum performance and maximum efficiency of the fan impeller, finding a dependence for the blade thickness to ensure its sufficient strength when operating at peripheral blade edge speeds exceeding the speed of sound.
- the fan blade contains a convex profile edge determined by geometric construction described by the radius of the circle Ria for the root part of the profile 3 of the blade and R16 for the end part of the blade 4; the leading edge of the blade 1 and the trailing edge of the blade 2 are made straight;
- Fig. 1 is an isometric view of a fan blade wheel
- Fig. 2 is a main view of a blade wheel with the main dimensions of the blade end profile indicated
- Fig. 3 is a view of a blade wheel from the right with the diameter designations and the location of the root section indicated
- Fig. 4 is a root section of a blade with the main dimensions indicated.
- the proposed technical solution for the profile of the fan blade of a turbojet engine allows the blade wheel to be made in one piece using, for example, a CNC milling machine with four degrees of freedom or more, which is currently a widespread technological process, reducing the cost of producing a fan wheel to a minimum, while ensuring high rigidity of the fan wheel and, as a result, ensuring the possibility of its operation at high, even supersonic at the edge, peripheral speeds.
- the rigidity of the design also ensures the possibility of operating the fan at significant angular accelerations of the rotor during a rapid change in the operating mode of the turbojet engine.
- the choice of blade geometry within the boundaries of the given parameters allows obtaining the highest possible efficiency of the fan wheel.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
La présente invention se rapporte au domaine des soufflantes de moteurs à turbine à gaz. Le résultat technique est obtenu par l'utilisation de cette structure complète de pale en utilisant un angle variable d'inclinaison des cordes du profil par rapport à la direction du flux d'air depuis le bord vers la section de racine de la pale, dans une plage limitée de relations entre le diamètre externe de la roue de travail et le diamètre interne D2:D1; l'exécution structurelle du profil de la pale, décrit par des arcs de circonférences ayant des centres de sections sur la longueur de la pale se situant sur une droite, assure un simplicité relative des techniques de production; les angles d'inclinaisons des cordes du profil par rapport au flux sont fonction de la longueur de la corde; les rayons de la partie convexe de la section et les rayons de la partie racine ainsi que l'épaisseur de la pale dans la section racine et la section d'extrémité assurent un coefficient d'efficacité élevé de la pale à des vitesses dépassant la vitesse du son tout en assurant une résistance suffisante dans une grande plage de vitesses de rotation de la soufflante.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2023113086 | 2023-05-20 | ||
| RU2023113086A RU2023113086A (ru) | 2023-05-20 | Форма лопастей вентилятора |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO2024242589A2 true WO2024242589A2 (fr) | 2024-11-28 |
| WO2024242589A9 WO2024242589A9 (fr) | 2025-01-16 |
Family
ID=93590257
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/RU2024/000234 Ceased WO2024242589A2 (fr) | 2023-05-20 | 2024-07-19 | Forme de pales de soufflante |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2024242589A2 (fr) |
-
2024
- 2024-07-19 WO PCT/RU2024/000234 patent/WO2024242589A2/fr not_active Ceased
Also Published As
| Publication number | Publication date |
|---|---|
| WO2024242589A9 (fr) | 2025-01-16 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 121 | Ep: the epo has been informed by wipo that ep was designated in this application |
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