RU2000130594A - Profiled compressor shovel with double bend - Google Patents

Profiled compressor shovel with double bend

Info

Publication number
RU2000130594A
RU2000130594A RU2000130594/06A RU2000130594A RU2000130594A RU 2000130594 A RU2000130594 A RU 2000130594A RU 2000130594/06 A RU2000130594/06 A RU 2000130594/06A RU 2000130594 A RU2000130594 A RU 2000130594A RU 2000130594 A RU2000130594 A RU 2000130594A
Authority
RU
Russia
Prior art keywords
blade
shank
axis
stacking
low pressure
Prior art date
Application number
RU2000130594/06A
Other languages
Russian (ru)
Other versions
RU2228461C2 (en
Inventor
Хсин-Туан ЛИУ
Роберт Б. ДИКМАН
Кеннет Уильям КРАБАЧЕР
Грегори Тодд ШТЕЙНМЕТЦ
Брент Франклин БИЧЕР
Брайан Кейт ДОЛОРЕСКО
Original Assignee
Дженерал Электрик Компани
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 to US09/455,826 priority Critical patent/US6331100B1/en
Priority to US09/455,826 priority
Application filed by Дженерал Электрик Компани filed Critical Дженерал Электрик Компани
Publication of RU2000130594A publication Critical patent/RU2000130594A/en
Application granted granted Critical
Publication of RU2228461C2 publication Critical patent/RU2228461C2/en

Links

Claims (14)

1. A profiled compressor blade 12 for an impeller disk 14 having axial, tangential and radial orthogonal axes, comprising high and low pressure sides 18, 20 extending radially from the shank 22 to the apex 24 and in the axial direction between the front and rear edges 26, 28, cross sections having respective chords and bending lines extending between the leading and trailing edges, and centers of gravity 34 aligned with the stacking axis 36 having a double bend, the low pressure side 20 curved along the trailing edge near the shank 22 to reduce the separation of flow on it.
 2. The blade according to claim 1, wherein the stacking axis contains two orthogonal components, including the stacking tangential axis 36a and the stacking axial axis 36b, wherein the stacking tangential axis is curved adjacent to the blade shaft 22 to give a bend to the low pressure side 20 at this location .
 3. The blade according to claim 2, in which the tangential axis 36a of the stacking includes a first bend 38 having an initial deflection forward from the shank 22 to the high pressure side 18, and a second bend 40 connected to the first bend and tilting back to the low pressure side 20 side by side with apex 24, and the zigzag arrangement of the sections next to the shank is changed to give a bend to the low pressure side at this point.
 4. The blade according to claim 3, in which the deflection forward is a deviation in the direction of rotation of the profiled blade on the disk 14, and the deviation back is a direction opposite to the direction of rotation.
 5. The blade according to claim 3, in which the trailing edge 28 is oriented essentially perpendicular to the shank on the curved side 20 of the low pressure and tilted back above it.
 6. The blade according to claim 3, in which the first and second bends 38, 40 are located on opposite sides of the radial axis passing through the shank 22 of the blade.
 7. The shoulder blade according to claim 3, in which the zigzag increases from the shank to the apex.
 8. The blade according to claim 3, in which the tangential axis of the stacking is essentially S-shaped from the shank to the apex.
 9. The blade according to claim 3, in which the trailing edge 28 is essentially S-shaped from the shank to the apex.
 10. A profiled compressor blade 12 for an impeller disk 14 having axial, tangential, and radial orthogonal axes, comprising high and low pressure sides 18, 20 extending radially from the shank 22 to the apex 24 and in the axial direction between the front and rear edges 26, 28, cross sections having respective chords and bending lines extending between the leading and trailing edges, and centers of gravity 34 aligned with the stacking axis 36 having a double bend, the low pressure side 20 The curvature axis is curved along the trailing edge 28 adjacent to the liner 22 to reduce flow separation on it, in which the stacking axis has two orthogonal components including the stacking tangential axis 36a and the stacking axial axis 36b, and has a double bend to give the bend a low side pressure along the trailing edge near the shank 22.
 11. A profiled blade 12 for the compressor impeller, comprising a double-bent piling axis 36 and a low pressure side bent along the trailing edge 28 adjacent to the shank 28 to reduce flow separation thereon.
 12. The blade of claim 11, wherein the stacking axis is substantially S-shaped and the trailing edge is substantially S-shaped.
 13. The blade according to claim 12, in which the trailing edge 28 is oriented essentially perpendicular to the shank on the curved side of the low pressure.
 14. The blade according to claim 13, in which the trailing edge 28 is deflected from the curved side of the low pressure to the top of the blade.
RU2000130594/06A 1999-12-06 2000-12-05 Double-bend formed-to-shape blade of compressor RU2228461C2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US09/455,826 US6331100B1 (en) 1999-12-06 1999-12-06 Doubled bowed compressor airfoil
US09/455,826 1999-12-06

Publications (2)

Publication Number Publication Date
RU2000130594A true RU2000130594A (en) 2003-01-27
RU2228461C2 RU2228461C2 (en) 2004-05-10

Family

ID=23810426

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2000130594/06A RU2228461C2 (en) 1999-12-06 2000-12-05 Double-bend formed-to-shape blade of compressor

Country Status (9)

Country Link
US (1) US6331100B1 (en)
EP (1) EP1106836B1 (en)
JP (1) JP4771585B2 (en)
KR (1) KR100827055B1 (en)
CN (1) CN1311144C (en)
CA (1) CA2326424C (en)
DE (1) DE60039957D1 (en)
PL (1) PL196777B1 (en)
RU (1) RU2228461C2 (en)

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