JPS5669404A - Turbine blade train - Google Patents

Turbine blade train

Info

Publication number
JPS5669404A
JPS5669404A JP14336779A JP14336779A JPS5669404A JP S5669404 A JPS5669404 A JP S5669404A JP 14336779 A JP14336779 A JP 14336779A JP 14336779 A JP14336779 A JP 14336779A JP S5669404 A JPS5669404 A JP S5669404A
Authority
JP
Japan
Prior art keywords
blades
protruded
passage
loss
secondary flow
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.)
Pending
Application number
JP14336779A
Other languages
Japanese (ja)
Inventor
Tadashi Fujiwara
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.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
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
Application filed by Hitachi Ltd filed Critical Hitachi Ltd
Priority to JP14336779A priority Critical patent/JPS5669404A/en
Publication of JPS5669404A publication Critical patent/JPS5669404A/en
Pending legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: To reduce the secondary flow loss and an attack angle loss, by providing protruded blades at the outlet portion of each static stationary blade between an inner and an outer diaphragm rings to form a throat smaller than that of a fluid passage between the stationary blades.
CONSTITUTION: Protruded blades 12 are provided at the outlet portion of each stationary blade 8 between an outer and an inner diaphragm rings 10, 11. The throat length l of the protruded blades 12 is made smaller than that L of the stationary blades 8. The radial lengths hT, hR of the protruded blades 12 are located in the secondary flow region. A working fluid near the walls of the diaphragms flow as shown by streamlines 14. The working fluid flows into a passage 16 while producing corner vortexes 15. Since the throat length l is smaller than the other throat length L, the fluid is accelerated in the passage 16 so that the corner vortexes 15 are weakened. This results in reducing the secondary flow loss and an attack angle loss.
COPYRIGHT: (C)1981,JPO&Japio
JP14336779A 1979-11-07 1979-11-07 Turbine blade train Pending JPS5669404A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP14336779A JPS5669404A (en) 1979-11-07 1979-11-07 Turbine blade train

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP14336779A JPS5669404A (en) 1979-11-07 1979-11-07 Turbine blade train

Publications (1)

Publication Number Publication Date
JPS5669404A true JPS5669404A (en) 1981-06-10

Family

ID=15337126

Family Applications (1)

Application Number Title Priority Date Filing Date
JP14336779A Pending JPS5669404A (en) 1979-11-07 1979-11-07 Turbine blade train

Country Status (1)

Country Link
JP (1) JPS5669404A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110014037A1 (en) * 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor with a flow pulse generator

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110014037A1 (en) * 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor with a flow pulse generator
US8591179B2 (en) * 2009-07-17 2013-11-26 Rolls-Royce Deutschland Ltd & Co Kg Axial-flow compressor with a flow pulse generator

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