WO2024248663A2 - Forme de pale de turbine - Google Patents

Forme de pale de turbine Download PDF

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Publication number
WO2024248663A2
WO2024248663A2 PCT/RU2024/000241 RU2024000241W WO2024248663A2 WO 2024248663 A2 WO2024248663 A2 WO 2024248663A2 RU 2024000241 W RU2024000241 W RU 2024000241W WO 2024248663 A2 WO2024248663 A2 WO 2024248663A2
Authority
WO
WIPO (PCT)
Prior art keywords
blade
turbine
profile
airfoil
blades
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
Application number
PCT/RU2024/000241
Other languages
English (en)
Russian (ru)
Other versions
WO2024248663A3 (fr
Inventor
Владислав Викторович МАТАФОНОВ
Андрей Юрьевич ХОЛОСТЕНКО
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from RU2023113882A external-priority patent/RU2837825C2/ru
Application filed by Individual filed Critical Individual
Priority to CN202480030375.4A priority Critical patent/CN121285679A/zh
Publication of WO2024248663A2 publication Critical patent/WO2024248663A2/fr
Publication of WO2024248663A3 publication Critical patent/WO2024248663A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • F01D5/14—Form or construction

Definitions

  • the invention relates to turbine blades of turbojet engines. Its application is most effective in low-power fan turbojet dual-circuit engines with a thrust of 1000 to 5000 N.
  • a turbojet engine contains a turbine that sets the engine rotor in motion.
  • turbine blades There are three types of turbine blades: active, reactive, and active-reactive.
  • the most widely used type of blade profile in turbojet engines is the active-reactive type.
  • the operation of a turbine with an active type of blade profile is characterized by lower operating peripheral speeds and lower efficiency compared to a reactive profile.
  • the turbine wheel consists of a base on which a multitude of profiled blades are fixed, which form a single structure with the base.
  • the need for low-power dual-circuit fan engines of 1000-5000 N has led to the need to improve the profile of the turbine blades, simplify the design of the engine turbine while maintaining a sufficiently high efficiency.
  • the most critical for the efficiency of the turbine and labor-intensive to manufacture is its wheel with a large number of blades of a complex profile.
  • a design of a turbine blade of an active-reactive type is known (Invention Certificate RU 2 498 082 C2).
  • a single-crystal turbine blade is manufactured by casting with directional crystallization and contains a blade airfoil, a final structural element of the blade airfoil, and a transition zone.
  • the blade airfoil has a leading and trailing edge, C-shaped trough and C-shaped back sides, a midline, and a longitudinal axis.
  • the final structural element of the blade airfoil contains the final side of the blade airfoil on the gas-air tract side, forming an angle with the longitudinal axis of the blade airfoil.
  • the transition zone is located between the blade airfoil and the final side of the blade airfoil and forms a thickening of the blade airfoil.
  • the transition zone extends around the leading edge between a point located on the back of the blade airfoil and on the end side of the end structural element of the blade airfoil upstream of the back of the C-shaped form, and a point located on the trough of the blade airfoil and on the end side of the end structural element of the blade airfoil upstream of the trough of the C-shaped form.
  • the disadvantage of this design is the technological complexity of manufacturing the blade, the need to use a blade specialized for this task technological equipment. Efficiency of using a blade at a relatively high peripheral speed.
  • a design of a turbine blade of an active-reactive type is known (Invention Certificate RU 2 383 748 C2).
  • the feather of a guide or nozzle blade, or a working blade of a blade machine, primarily a gas turbine, has at least one thickening of its profile on its radially inner end section and/or on its radially outer end section, which has a positive effect on the aerohydrodynamic characteristics.
  • the thickening is made cut in the area of the leading edge of the blade feather to form a front surface, respectively, a base surface.
  • the thickening is made in the area of the leading edge of the blade feather with a cut having a surface in the form of a circular or cylindrical segment.
  • the invention is aimed at creating a blade having improved aerodynamic characteristics.
  • a turbine blade design is known (Invention Certificate RU 2 342 538 C2).
  • the turbine blade includes an aerodynamic profile, a base, a root and a dovetail joint.
  • the blade has a nominal profile of the inner central part substantially in accordance with the X, Y and Z rectangular coordinate values given in Table I.
  • the Z values are dimensionless values from 0 to 1, converted to Z distances in inches by multiplying the Z values by the blade height in inches.
  • the X and Y values are distances in inches which, after being connected by smooth continuous arcs, define the sections of the profile of the inner central part at each Z distance along the blade.
  • the sections of the profile at Z distances are connected smoothly with each other to form the said profile of the inner central part of the blade.
  • the distances X, Y and Z can be proportionally changed depending on the same constant or number to obtain a proportionally increased or proportionally decreased profile of the inner central part.
  • the nominal profile of the inner central part, defined by the distances X, Y and Z, is laid on the envelope with an accuracy of ⁇ 0.039 inches in directions normal to any place on the surface of the inner central section.
  • the invention allows for improving aerodynamic efficiency.
  • the disadvantage of this design is the extremely complex production process.
  • the design of a turbine blade is known (invention certificate RU 2 178 086 C2).
  • the gas turbine blade has a profile part consisting of the contours of the back, trough and edges.
  • the contours of the back and trough are formed by sinusoidal spirals.
  • the invention allows to reduce energy losses in the blade crowns, reduce the time of blade profiling and expand the area of reliable construction of blade profiles.
  • a turbine blade design is known (invention certificate RU 2 518 767 C2) accepted for a number of features as the closest analogue.
  • the turbine wheel contains turbine blades containing a profile part having an aerodynamic shape.
  • This aerodynamic shape has a nominal profile corresponding to the data in the tables given in the description.
  • the coordinate values are smoothly connected by an arc of radius R to form a section of the profile part at each distance from the wheel rotation axis.
  • the sections of the profile are smoothly connected to each other to form a complete aerodynamic shape.
  • the proposed profile of the profile part of the blade ensures as a result an improvement in the efficiency and load-bearing capacity of the aerodynamic part and the blades as a whole.
  • the disadvantage of this design is the technological complexity of obtaining a smooth blade profile with a variable shape of its profile along the height of the blade; specialized technological equipment is required, which determines the high cost of blade production.
  • the objective of this invention is to develop a simple design of a turbine blade for low-power fan turbojet twin-circuit engines with a thrust of 1000 to 5000 N, which differs from its analogue in its simple manufacturing technology, efficient operation at low circumferential speeds, low manufacturing cost, and the possibility of manufacturing on universal process equipment with a relatively high efficiency.
  • the second claim of the invention allows for the production of single-crystal blades from a single crystal of aluminum oxide (Al2O3), which will increase the service life of the turbine blades and allow the working gas temperature to be raised by increasing the heat resistance of the blades.
  • Al2O3 aluminum oxide
  • the stated objective is achieved by using an active blade profile that is constant along its height with a profile constructed using characteristic base points shown in Fig.
  • the blade is manufactured by cutting from a single crystal of aluminum oxide (Al2O3), which allows increasing the working life of the turbine due to the greater heat resistance of the blades and the wear resistance of the single crystal of oxide.
  • Al2O3 aluminum oxide
  • Fig. 1 shows a typical view of a turbine wheel with blades of this shape.
  • Position (1) marks the surface of the blade that is most distant from the axis of rotation, position (2) the convex part of the blade, position (3) the concave part of the blade profile.
  • Fig. 2 contains the shape of the blade section with the positions of the nodal points, the interpolation of the surface between the points is performed by a quadratic spline.
  • This invention will allow to produce turbine blades operating at relatively low circumferential speeds using widespread, universal technological equipment, for example, 5-axis CNC milling machines, will ensure low cost of production of turbine wheels of turbojet engines.
  • the selected geometry of the blade allows to obtain maximum efficiency and high pressure under specified initial conditions.
  • the use of monocrystalline aluminum oxide (Al2O3) for the manufacture of blades according to the second point of the formula of the invention will increase the service life of the turbine blades and increase the temperature of the working fluid (combustion products), thus increasing the efficiency of the turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne des pales de travail de turbines de turboréacteurs. La pale de travail comprend une partie profilée de la surface externe et une partie profilée de la surface interne, qui possèdent une forme aérodynamique, avec un profil nominal construit sur des points de base caractéristiques; les points caractéristiques sont connectés régulièrement par une spline quadratique; la section du profil dans une direction suivant le rayon de la roue de la turbine est constante, la pale peut se composer de monocristal d'oxyde d'aluminium (Al2O3), et une pale donnée est fabriquée selon un procédé de découpe de monocristal. L'invention permet de simplifier la structure de la turbine, de réduire les coûts de production en assurant une efficacité suffisante dans une grande plage de vitesses de rotation, d'augmenter la température du gaz en amont de la turbine sans utiliser de canaux de refroidissement dans la pale.
PCT/RU2024/000241 2023-05-28 2024-07-26 Forme de pale de turbine Ceased WO2024248663A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202480030375.4A CN121285679A (zh) 2023-05-28 2024-07-26 涡轮叶片形状

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2023113882 2023-05-28
RU2023113882A RU2837825C2 (ru) 2023-05-28 Форма лопатки турбины

Publications (2)

Publication Number Publication Date
WO2024248663A2 true WO2024248663A2 (fr) 2024-12-05
WO2024248663A3 WO2024248663A3 (fr) 2025-01-30

Family

ID=93658103

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2024/000241 Ceased WO2024248663A2 (fr) 2023-05-28 2024-07-26 Forme de pale de turbine

Country Status (2)

Country Link
CN (1) CN121285679A (fr)
WO (1) WO2024248663A2 (fr)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2867223B1 (fr) * 2004-03-03 2006-07-28 Snecma Moteurs Turbomachine comme par exemple un turboreacteur pour avion
FR3023317B1 (fr) * 2014-07-04 2016-08-05 Snecma Procede de fabrication d'une aube bi-composant pour moteur a turbine a gaz et aube obtenue par un tel procede
JP6550000B2 (ja) * 2016-02-26 2019-07-24 三菱日立パワーシステムズ株式会社 タービン翼
RU2639584C1 (ru) * 2016-07-01 2017-12-21 Публичное акционерное общество "Научно-производственное объединение "Сатурн" Способ шлифования криволинейных поверхностей детали на робототехнологическом комплексе
RU178050U1 (ru) * 2017-11-10 2018-03-21 Акционерное общество "Уральский турбинный завод" Рабочая лопатка постоянного профиля с цельнофрезерованным бандажом с сохранением выходной площади при изготовлении

Also Published As

Publication number Publication date
WO2024248663A3 (fr) 2025-01-30
CN121285679A (zh) 2026-01-06

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