SU779591A1 - Turbomachine impeller - Google Patents
Turbomachine impeller Download PDFInfo
- Publication number
- SU779591A1 SU779591A1 SU782697334A SU2697334A SU779591A1 SU 779591 A1 SU779591 A1 SU 779591A1 SU 782697334 A SU782697334 A SU 782697334A SU 2697334 A SU2697334 A SU 2697334A SU 779591 A1 SU779591 A1 SU 779591A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- blade
- impeller
- turbomachine
- turbomachine impeller
- interscapular
- Prior art date
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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
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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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/29—Three-dimensional machined; miscellaneous
- F05D2250/294—Three-dimensional machined; miscellaneous grooved
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
1one
Изобретение относитс к лопаточным машинам и может быть использовано в паровых и газовых турбинах.The invention relates to blade machines and can be used in steam and gas turbines.
Известно рабочее колесо турбомашины , содержащее лотгатки, образующие 5 мёжлопаточные каналы, и имеющие продольную конфузорную прорезь l.A turbomachine impeller is known, containing lozgatki, forming 5 hopper channels, and having a longitudinal confused slot l.
Однако в указанной конструкции рабочего колеса продольна конфу орна прорезь имеет высоту, практичес- 10 ни равную длине лопатки, а площадь ее выходного сечени и выходной угол между ее осью и спинкой лопатки оптимизированы Ь основными геометричесКИМ11 параметрами профил лопатки f5 лишь с точки зрени получени максимального качества собственно профил , чтовызывает повышение утечки в радиальном зазоре и снижает, тем самым КПД турбомашины..20However, in this design of the impeller, the longitudinal edge of the ornament has a height practically equal to the length of the blade, and the area of its output cross section and the output angle between its axis and the back of the blade are optimized by the basic geometry parameters of the blade profile f5 only from the point of view of obtaining maximum quality the actual profile, which causes an increase in leakage in the radial gap and reduces, thereby, the efficiency of the turbomachine.
Цель изобретени - повышение КПД турбомашины.The purpose of the invention is to increase the efficiency of the turbomachine.
Указанна цель достигаетс тем, что кажда прорезь имеет высоту, составл ющую 0,05-0,12 от длины лопат- 25 ки, площадь выходного сечени 0 ,0005-0,0035 от площади горла межлопаточного канала и выходной угол между ее осью и спинкой лопатки со , стороны выходной кромки, равный 5-4S.30This goal is achieved by the fact that each slot has a height of 0.05-0.12 of the length of the blade, an output section of 0,0005-0.0035 of the throat of the interscapular channel, and an exit angle between its axis and back. blades from the side of the exit edge, equal to 5-4S.30
На фиг. 1 дана лопатка,- общий вид; на фиг. 2 - развертка рабочего колеса на плоскость вращени .FIG. 1 given shovel, - a general view; in fig. 2 shows an impeller sweep onto the plane of rotation.
Рабочее колесо турбомашины содержит лопатки 1, образующие межлопаточные каналы 2 и имеющие продольную конфузорную прорезь 3., Кажда прорезь 3 имеет высоту h, составл ющую 0,05-0,12 от длины L лопатки 1, площадь выходного сечени - 0,00050 ,0035 от площади горла межлопаточного канала 2 и выходной угол ot между ее осью и спинкой лопатки 1 со стороHtJ ВЫ340ДНОЙ кромки 4, равный 5-45.The turbomachine impeller contains blades 1, forming interscapular channels 2 and having a longitudinal confused recess 3. Each slot 3 has a height h of 0.05-0.12 from the length L of the blade 1, the area of the output section is 0.00050, 0035 from the area of the throat of the interscapular canal 2 and the output angle ot between its axis and the back of the shoulder blade 1 on the side of the upper edge 4, equal to 5-45.
При вращении рабочего колеса создаетс перепад давлений потока газа между корытом и стенкой профил лопаток 1. В этих услови х конфузорна прорезь 3 с корыта на спинку лопатки 1 в концевой зоне формирует высокоскоростную струю рабочего тела, разгон ющую подторможенный пограничный слой, что не дает ему оторватьс .When the impeller rotates, a pressure drop of the gas flow between the trough and the wall of the blade section 1 is created. Under these conditions, a confused slit 3 from the trough to the back of the blade 1 in the end zone forms a high-speed jet of the working fluid, which accelerates the retarded boundary layer, which prevents it from tearing .
Такое выполнение рабочего колеса, уменьшает потери в радиальном зазоре и перетечки рабочего тела в межлопаточном канапе, что повышает КПД турбомашины.This embodiment of the impeller reduces the loss in the radial clearance and overflow of the working fluid in the interscapular canapes, which increases the efficiency of the turbomachine.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU782697334A SU779591A1 (en) | 1978-12-14 | 1978-12-14 | Turbomachine impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU782697334A SU779591A1 (en) | 1978-12-14 | 1978-12-14 | Turbomachine impeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU779591A1 true SU779591A1 (en) | 1980-11-15 |
Family
ID=20798826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU782697334A SU779591A1 (en) | 1978-12-14 | 1978-12-14 | Turbomachine impeller |
Country Status (1)
| Country | Link |
|---|---|
| SU (1) | SU779591A1 (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4497613A (en) * | 1983-01-26 | 1985-02-05 | General Electric Company | Tapered core exit for gas turbine bucket |
| US4636143A (en) * | 1984-06-29 | 1987-01-13 | Otto Zeides | Propeller for gaseous and fluidic media |
| FR2623569A1 (en) * | 1987-11-19 | 1989-05-26 | Snecma | VANE OF COMPRESSOR WITH DISSYMMETRIC LETTLE LETCHES |
| EP1013878A3 (en) * | 1998-12-21 | 2002-01-02 | General Electric Company | Twin rib turbine blade |
| EP2309098A1 (en) * | 2009-09-30 | 2011-04-13 | Siemens Aktiengesellschaft | Airfoil and corresponding guide vane, blade, gas turbine and turbomachine |
| EP2378075A1 (en) * | 2010-04-19 | 2011-10-19 | Rolls-Royce plc | Rotor blade and corresponding gas turbine engine |
| EP2378074A1 (en) * | 2010-04-19 | 2011-10-19 | Rolls-Royce plc | Rotor blade and corresponding gas turbine engine |
| CN106460527A (en) * | 2014-06-25 | 2017-02-22 | 西门子股份公司 | Compressor aerofoil and corresponding compressor rotor assembly |
| RU2692938C1 (en) * | 2014-08-05 | 2019-06-28 | Сафран Эркрафт Энджинз | Turbine blade, turbine disk and gas turbine engine turbine |
-
1978
- 1978-12-14 SU SU782697334A patent/SU779591A1/en active
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4497613A (en) * | 1983-01-26 | 1985-02-05 | General Electric Company | Tapered core exit for gas turbine bucket |
| US4636143A (en) * | 1984-06-29 | 1987-01-13 | Otto Zeides | Propeller for gaseous and fluidic media |
| FR2623569A1 (en) * | 1987-11-19 | 1989-05-26 | Snecma | VANE OF COMPRESSOR WITH DISSYMMETRIC LETTLE LETCHES |
| US4875831A (en) * | 1987-11-19 | 1989-10-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Compressor rotor blade having a tip with asymmetric lips |
| EP1013878A3 (en) * | 1998-12-21 | 2002-01-02 | General Electric Company | Twin rib turbine blade |
| EP2309098A1 (en) * | 2009-09-30 | 2011-04-13 | Siemens Aktiengesellschaft | Airfoil and corresponding guide vane, blade, gas turbine and turbomachine |
| EP2378075A1 (en) * | 2010-04-19 | 2011-10-19 | Rolls-Royce plc | Rotor blade and corresponding gas turbine engine |
| EP2378074A1 (en) * | 2010-04-19 | 2011-10-19 | Rolls-Royce plc | Rotor blade and corresponding gas turbine engine |
| US8845280B2 (en) | 2010-04-19 | 2014-09-30 | Rolls-Royce Plc | Blades |
| US8851833B2 (en) | 2010-04-19 | 2014-10-07 | Rolls-Royce Plc | Blades |
| CN106460527A (en) * | 2014-06-25 | 2017-02-22 | 西门子股份公司 | Compressor aerofoil and corresponding compressor rotor assembly |
| US10267330B2 (en) | 2014-06-25 | 2019-04-23 | Siemens Aktiengesellschaft | Compressor aerofoil and corresponding compressor rotor assembly |
| RU2692938C1 (en) * | 2014-08-05 | 2019-06-28 | Сафран Эркрафт Энджинз | Turbine blade, turbine disk and gas turbine engine turbine |
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