SU566942A1 - Arrangement for delivery of exhaust gases of an internal combustion engine to a turbocompressor - Google Patents
Arrangement for delivery of exhaust gases of an internal combustion engine to a turbocompressorInfo
- Publication number
- SU566942A1 SU566942A1 SU7402081649A SU2081649A SU566942A1 SU 566942 A1 SU566942 A1 SU 566942A1 SU 7402081649 A SU7402081649 A SU 7402081649A SU 2081649 A SU2081649 A SU 2081649A SU 566942 A1 SU566942 A1 SU 566942A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- partition
- thickness
- combustion engine
- internal combustion
- exhaust gases
- Prior art date
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Supercharger (AREA)
Description
входа потока на колесо, что приводит к снижению действующих на колесо возмущающих сил.the entrance of the flow to the wheel, which leads to a decrease in the disturbing forces acting on the wheel.
На фиг. 1 изображена турбина с безлопаточным наиравл ющим аниаратом и разделительными иерегородками; на фиг. 2 - участок разделительной иерегородки, примыкающий к рабочему колесу ( в увеличенном масштабе).FIG. Figure 1 shows a turbine with a bezoolepatny naraiuyu aniarata and separating sites; in fig. 2 - a section of the separation wall adjacent to the impeller (on an enlarged scale).
В общем корпусе 1 турбины размещено центростремительное колесо 2 и охватывающие его спиральные каналы 3 и 4 безлопаточного направл ющего аппарата. Каналы отделены один от другого при помощи перегородок 5 и 6 с выпуклыми наружными 7 и вогнутыми внутренними 8 поверхност ми. Части 9 и 10 этих перегородок, примыкающие к рабочему колесу , выполнены криволинейными, причем части 9 и 10 вогнутой поверхности перегородок выполнены с увеличенной толщиной. Максимальна толщина перегородки составл ет 1,1-1,6 от номинальной. Выпукла и вогнута поверхности перегородок образуют углы ai и 1062 с тангенциальной составл ющей скорости потока, а максимальный угол Y между касательными к выпуклой и вогнутой поверхност м , равный разности углов «2 и «i, лежит в пределах10-30°.The centripetal wheel 2 and the spiral channels 3 and 4 covering it without a blade guiding device are located in the general housing 1 of the turbine. The channels are separated from one another by partitions 5 and 6 with convex outer 7 and concave inner 8 surfaces. Parts 9 and 10 of these partitions, adjacent to the impeller, are curved, and part 9 and 10 of the concave surface of the partitions are made with increased thickness. The maximum thickness of the septum is 1.1-1.6 of the nominal. The convex and concave surfaces of the partitions form angles ai and 1062 with the tangential component of the flow velocity, and the maximum angle Y between the tangents to the convex and concave surfaces, equal to the difference of the angles 2 2 and i i, lies in the range 10–30 °.
Устройство работает следующим образом.The device works as follows.
Между част ми 9 и 10 перегородок и колесом имеетс зазор, через который часть газов перепускаетс из одного канала в другой, в результате чего уменьшаетс скачок давлени при нереходе лопатки колеса 2 мимо разделительной перегородки. Вследст1вие переменной толщины перегородки и переменного сечени зазо.ра сохран етс посто нным угол входа потока на колесо, уменьшаютс потери при перетекании газа и плавно измен етс давление газов, действующих на колесо 2.Between parts 9 and 10 of the barriers and a wheel there is a gap through which a part of the gases is bypassed from one channel to another, as a result of which the pressure jump decreases as the blade 2 of the wheel 2 passes by the barriers. Due to the variable thickness of the partition and the variable cross section of the gap, the angle of entry of the flow onto the wheel is kept constant, the losses due to the flow of gas are reduced, and the pressure of the gases acting on wheel 2 smoothly changes.
Claims (3)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU7402081649A SU566942A1 (en) | 1974-12-04 | 1974-12-04 | Arrangement for delivery of exhaust gases of an internal combustion engine to a turbocompressor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU7402081649A SU566942A1 (en) | 1974-12-04 | 1974-12-04 | Arrangement for delivery of exhaust gases of an internal combustion engine to a turbocompressor |
Publications (1)
Publication Number | Publication Date |
---|---|
SU566942A1 true SU566942A1 (en) | 1977-07-30 |
Family
ID=20602754
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU7402081649A SU566942A1 (en) | 1974-12-04 | 1974-12-04 | Arrangement for delivery of exhaust gases of an internal combustion engine to a turbocompressor |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU566942A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4473931A (en) * | 1982-03-24 | 1984-10-02 | Nissan Motor Company, Ltd. | Method of producing a turbine casing |
US6913439B2 (en) * | 2002-01-22 | 2005-07-05 | Dr. Ing. H.C.F. Porsche Ag | Exhaust gas turbocharger for an internal-combustion engine |
RU2570989C2 (en) * | 2012-07-10 | 2015-12-20 | Альстом Текнолоджи Лтд | Gas turbine combustion chamber axial swirler |
-
1974
- 1974-12-04 SU SU7402081649A patent/SU566942A1/en active
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4473931A (en) * | 1982-03-24 | 1984-10-02 | Nissan Motor Company, Ltd. | Method of producing a turbine casing |
US6913439B2 (en) * | 2002-01-22 | 2005-07-05 | Dr. Ing. H.C.F. Porsche Ag | Exhaust gas turbocharger for an internal-combustion engine |
RU2570989C2 (en) * | 2012-07-10 | 2015-12-20 | Альстом Текнолоджи Лтд | Gas turbine combustion chamber axial swirler |
US9518740B2 (en) | 2012-07-10 | 2016-12-13 | General Electric Company Gmbh | Axial swirler for a gas turbine burner |
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