JPS55104529A - Power recovering turbine - Google Patents

Power recovering turbine

Info

Publication number
JPS55104529A
JPS55104529A JP964779A JP964779A JPS55104529A JP S55104529 A JPS55104529 A JP S55104529A JP 964779 A JP964779 A JP 964779A JP 964779 A JP964779 A JP 964779A JP S55104529 A JPS55104529 A JP S55104529A
Authority
JP
Japan
Prior art keywords
gas
turbine
passage
dust
discharged
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
JP964779A
Other languages
Japanese (ja)
Inventor
Takeshi Murakami
Nobuyuki Yamaguchi
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries 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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP964779A priority Critical patent/JPS55104529A/en
Publication of JPS55104529A publication Critical patent/JPS55104529A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE: To prolong the service life of a power recovering turbine in which high- pressure, dust-containing gas is used as work fluid, by minimizing wear of blades caused by dust through provision of an annular suction passage which is capable of causing deflection of solid particles contained in waste gas by way of centrifugal separation.
CONSTITUTION: Gas is introduced into inlet port 01 of a power recovering turbine in the direction shown by arrow in the drawing. Then, gas flow is curved inwards while being accelerated at restricted inlet passage 02 and thus deflected gradually into the axial direction. The gas flow is then divided annularly into outer and inner passages 03, 11. Gas introduced into the outer passage 03 flows into main turbine rotated at a high circumferential speed and discharged from outlet 05 via exhaust- gas diffuser 04. Gas introduced into the inner passage 11, on the other hand, is carried through the front suction chamber of subsidiary turbine into the subsidiary turbine and then discharged to the outside from outlet 13. Here, dust (solid particles) contained in the gas is deflected toward the wall 22 of inlet passage 02 while the gas flow is accelerated in passage 02 and deflected gradually into the axial direction, so that most part Y of dust is discharged through subsidiary turbine.
COPYRIGHT: (C)1980,JPO&Japio
JP964779A 1979-02-01 1979-02-01 Power recovering turbine Pending JPS55104529A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP964779A JPS55104529A (en) 1979-02-01 1979-02-01 Power recovering turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP964779A JPS55104529A (en) 1979-02-01 1979-02-01 Power recovering turbine

Publications (1)

Publication Number Publication Date
JPS55104529A true JPS55104529A (en) 1980-08-11

Family

ID=11726003

Family Applications (1)

Application Number Title Priority Date Filing Date
JP964779A Pending JPS55104529A (en) 1979-02-01 1979-02-01 Power recovering turbine

Country Status (1)

Country Link
JP (1) JPS55104529A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4050196A1 (en) * 2021-02-18 2022-08-31 Pratt & Whitney Canada Corp. Inertial particle separator for a turbine section of a gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4050196A1 (en) * 2021-02-18 2022-08-31 Pratt & Whitney Canada Corp. Inertial particle separator for a turbine section of a gas turbine engine

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