EP2143956A3 - Flow work machine with groove on a running gap of a blade end - Google Patents
Flow work machine with groove on a running gap of a blade end Download PDFInfo
- Publication number
- EP2143956A3 EP2143956A3 EP09007629.0A EP09007629A EP2143956A3 EP 2143956 A3 EP2143956 A3 EP 2143956A3 EP 09007629 A EP09007629 A EP 09007629A EP 2143956 A3 EP2143956 A3 EP 2143956A3
- Authority
- EP
- European Patent Office
- Prior art keywords
- groove
- blade end
- gap
- work machine
- flow work
- 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.)
- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Die Erfindung betrifft eine Strömungsarbeitsmaschine mit einem von einer Nabe (3) und einem Gehäuse (1) berandeten Hauptströmungspfad (2), in welchem mindestens eine Reihe von Schaufeln (5) angeordnet ist, wobei an mindestens einer Schaufelreihe (5) zwischen einem Schaufelende und einer Hauptströmungspfadberandung ein Spalt (11) vorgesehen ist, wobei das Schaufelende und die Hauptströmungspfadberandung eine rotierende Relativbewegung zueinander ausführen und im Bereich des Spaltes (11) in der Hauptströmungspfadberandung mindestens eine Nut (7) entlang mindestens eines Teils des Umfangs vorgesehen ist, wobei die Querschnittsfläche der Nut (7) in der Meridianansicht der Strömungsarbeitsmaschine betrachtet wesentlich von einer Parallelogrammform abweicht und aufgrund seiner Konturgebung stromaufwärts geneigt ist, dadurch gekennzeichnet, dass der Schwerpunkt des Nutquerschnittsfläche stromauf des Mittelpunktes der Nutöffnung (12) am Hauptströmungspfad vorgesehen ist. The invention relates to a turbomachine having a main flow path (2) bordered by a hub (3) and a housing (1), in which at least one row of blades (5) is arranged, wherein at least one blade row (5) is arranged between a blade end and a main flow path boundary a gap (11) is provided, wherein the blade end and the Hauptströmungspfadberandung perform a rotating relative movement to each other and in the region of the gap (11) in the Hauptströmungspfadberandung at least one groove (7) along at least part of the circumference is provided, wherein the cross-sectional area the groove (7) viewed in the meridian view of the fluid flow machine is substantially deviated from a parallelogram shape and inclined upstream due to its contouring, characterized in that the center of gravity of the groove cross-sectional area is provided upstream of the center of the groove opening (12) on the main flowpath.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008031982A DE102008031982A1 (en) | 2008-07-07 | 2008-07-07 | Turbomachine with groove at a trough of a blade end |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2143956A2 EP2143956A2 (en) | 2010-01-13 |
EP2143956A3 true EP2143956A3 (en) | 2015-03-18 |
Family
ID=41037780
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09007629.0A Withdrawn EP2143956A3 (en) | 2008-07-07 | 2009-06-09 | Flow work machine with groove on a running gap of a blade end |
Country Status (3)
Country | Link |
---|---|
US (1) | US8257022B2 (en) |
EP (1) | EP2143956A3 (en) |
DE (1) | DE102008031982A1 (en) |
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US9812047B2 (en) * | 2010-02-25 | 2017-11-07 | Manufacturing Resources International, Inc. | System and method for remotely monitoring the operating life of electronic displays |
EP2535598B1 (en) * | 2010-02-09 | 2018-06-06 | IHI Corporation | Centrifugal compressor using an asymmetric self-recirculating casing treatment |
JP5430683B2 (en) * | 2010-02-09 | 2014-03-05 | 株式会社Ihi | Centrifugal compressor with non-axisymmetric self-circulating casing treatment |
JP5430685B2 (en) * | 2010-02-09 | 2014-03-05 | 株式会社Ihi | Centrifugal compressor with non-axisymmetric self-circulating casing treatment |
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US8550768B2 (en) * | 2010-06-08 | 2013-10-08 | Siemens Energy, Inc. | Method for improving the stall margin of an axial flow compressor using a casing treatment |
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DE102011006275A1 (en) | 2011-03-28 | 2012-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Stator of an axial compressor stage of a turbomachine |
DE102011006273A1 (en) | 2011-03-28 | 2012-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Rotor of an axial compressor stage of a turbomachine |
DE102011007767A1 (en) * | 2011-04-20 | 2012-10-25 | Rolls-Royce Deutschland Ltd & Co Kg | flow machine |
FR2981131B1 (en) * | 2011-10-07 | 2013-11-01 | Turbomeca | CENTRIFUGAL COMPRESSOR EQUIPPED WITH A WEAR MEASUREMENT MARKER AND WEAR FOLLOWING METHOD USING THE MARKER |
US9068507B2 (en) * | 2011-11-16 | 2015-06-30 | General Electric Company | Compressor having purge circuit and method of purging |
JP5853721B2 (en) * | 2012-01-23 | 2016-02-09 | 株式会社Ihi | Centrifugal compressor |
FR2989742B1 (en) * | 2012-04-19 | 2014-05-09 | Snecma | UPRIGHT CAVITY COMPRESSOR HOUSING OPTIMIZED |
DE112013003306B4 (en) | 2012-07-26 | 2023-04-06 | Borgwarner Inc. | Compressor cover with circumferential groove |
WO2014158236A1 (en) * | 2013-03-12 | 2014-10-02 | United Technologies Corporation | Cantilever stator with vortex initiation feature |
US9644639B2 (en) * | 2014-01-27 | 2017-05-09 | Pratt & Whitney Canada Corp. | Shroud treatment for a centrifugal compressor |
EP2927503B1 (en) | 2014-04-03 | 2023-05-17 | MTU Aero Engines AG | Gas turbine compressor, aircraft engine and design method |
US10465716B2 (en) * | 2014-08-08 | 2019-11-05 | Pratt & Whitney Canada Corp. | Compressor casing |
WO2016022138A1 (en) * | 2014-08-08 | 2016-02-11 | Siemens Aktiengesellschaft | Compressor usable within a gas turbine engine |
CN104279181B (en) * | 2014-09-26 | 2017-06-06 | 清华大学 | Centrifugal pump impeller |
US20160153465A1 (en) * | 2014-12-01 | 2016-06-02 | General Electric Company | Axial compressor endwall treatment for controlling leakage flow therein |
US10539154B2 (en) | 2014-12-10 | 2020-01-21 | General Electric Company | Compressor end-wall treatment having a bent profile |
US10107307B2 (en) | 2015-04-14 | 2018-10-23 | Pratt & Whitney Canada Corp. | Gas turbine engine rotor casing treatment |
US10487847B2 (en) | 2016-01-19 | 2019-11-26 | Pratt & Whitney Canada Corp. | Gas turbine engine blade casing |
FR3065482B1 (en) * | 2017-04-20 | 2019-07-05 | Safran Aircraft Engines | SEAL RING MEMBER FOR TURBINE COMPRISING A CAVITY INCLINED IN ABRADABLE MATERIAL |
DE102018203304A1 (en) | 2018-03-06 | 2019-09-12 | MTU Aero Engines AG | Gas turbine compressor |
CN108506249B (en) * | 2018-04-02 | 2020-03-10 | 华能国际电力股份有限公司 | Groove end wall processing method for axial flow compressor |
US10876423B2 (en) * | 2018-12-28 | 2020-12-29 | Honeywell International Inc. | Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section |
US10914318B2 (en) | 2019-01-10 | 2021-02-09 | General Electric Company | Engine casing treatment for reducing circumferentially variable distortion |
US11015465B2 (en) * | 2019-03-25 | 2021-05-25 | Honeywell International Inc. | Compressor section of gas turbine engine including shroud with serrated casing treatment |
US11078805B2 (en) * | 2019-04-15 | 2021-08-03 | Raytheon Technologies Corporation | Inclination of forward and aft groove walls of casing treatment for gas turbine engine |
EP3734081A1 (en) * | 2019-04-30 | 2020-11-04 | Borgwarner Inc. | Flow modification device for compressor |
JP2021124069A (en) * | 2020-02-06 | 2021-08-30 | 三菱重工業株式会社 | Compressor housing, compressor with compressor housing, and turbocharger with compressor |
US20230151825A1 (en) * | 2021-11-17 | 2023-05-18 | Pratt & Whitney Canada Corp. | Compressor shroud with swept grooves |
CN114857086A (en) * | 2022-04-20 | 2022-08-05 | 新奥能源动力科技(上海)有限公司 | Axial flow compressor and gas turbine |
US12078070B1 (en) | 2023-08-16 | 2024-09-03 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with sliding doors for a fan of a gas turbine engine |
US12018621B1 (en) | 2023-08-16 | 2024-06-25 | Rolls-Royce North American Technologies Inc. | Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine |
US11970985B1 (en) | 2023-08-16 | 2024-04-30 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine |
US12085021B1 (en) | 2023-08-16 | 2024-09-10 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with movable closure for a fan of a gas turbine engine |
US11965528B1 (en) | 2023-08-16 | 2024-04-23 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with circumferential movable closure for a fan of a gas turbine engine |
US12066035B1 (en) | 2023-08-16 | 2024-08-20 | Rolls-Royce North American Technologies Inc. | Adjustable depth tip treatment with axial member with pockets for a fan of a gas turbine engine |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1008758A2 (en) * | 1998-12-10 | 2000-06-14 | United Technologies Corporation | Fluid compressors |
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-
2008
- 2008-07-07 DE DE102008031982A patent/DE102008031982A1/en not_active Withdrawn
-
2009
- 2009-06-09 EP EP09007629.0A patent/EP2143956A3/en not_active Withdrawn
- 2009-07-06 US US12/498,050 patent/US8257022B2/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1008758A2 (en) * | 1998-12-10 | 2000-06-14 | United Technologies Corporation | Fluid compressors |
Also Published As
Publication number | Publication date |
---|---|
EP2143956A2 (en) | 2010-01-13 |
DE102008031982A1 (en) | 2010-01-14 |
US20100014956A1 (en) | 2010-01-21 |
US8257022B2 (en) | 2012-09-04 |
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