EP3088672A1 - Procédé de conception d'un moteur à écoulement de fluide et moteur à écoulement de fluide - Google Patents

Procédé de conception d'un moteur à écoulement de fluide et moteur à écoulement de fluide Download PDF

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Publication number
EP3088672A1
EP3088672A1 EP15165253.4A EP15165253A EP3088672A1 EP 3088672 A1 EP3088672 A1 EP 3088672A1 EP 15165253 A EP15165253 A EP 15165253A EP 3088672 A1 EP3088672 A1 EP 3088672A1
Authority
EP
European Patent Office
Prior art keywords
slot
engine
gap
fluid flow
rotor
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Withdrawn
Application number
EP15165253.4A
Other languages
German (de)
English (en)
Inventor
Senthil Krishnababu
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP15165253.4A priority Critical patent/EP3088672A1/fr
Priority to US15/563,285 priority patent/US20180073381A1/en
Priority to EP16713423.8A priority patent/EP3289183A1/fr
Priority to PCT/EP2016/056963 priority patent/WO2016173793A1/fr
Priority to CN201680024609.XA priority patent/CN107532478B/zh
Publication of EP3088672A1 publication Critical patent/EP3088672A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps

Definitions

  • the invention relates to a fluid flow engine, in particular a compressor or a turbine of a gas turbine engine, having a stationary engine casing and a rotor assembly rotatable supported in the engine casing, the rotor assembly comprising at least one circumferentially extending rotor blade row with a plurality of radially extending unshrouded rotor blades, an inner surface of the engine casing comprising at least one circumferentially extending slot arranged radially outside of the rotor blade row, wherein a gap is provided between tips of the rotor blades and a base of said slot.
  • a fluid flow engine has a stationary engine casing and a rotor assembly rotatable supported in the engine casing.
  • the rotor assembly comprises at least one circumferentially extending rotor blade row with a plurality of radially extending unshrouded rotor blades.
  • a clearance gap is provided between tips of the rotor blades and an inner surface of the engine casing to prevent or at least reduce occurrence of a radial contact, in particular physical rubbing, between the tips and the inner surface as far as possible.
  • a temporary radial contact between blade tips and the inner surface of the engine casing may still occur.
  • a method according to the invention for designing a fluid flow engine, in particular a compressor or a turbine of a gas turbine engine, comprises the steps of:
  • Determination of the minimum gap height may include measuring of this minimum gap height at a conventional fluid flow engine or considering known values for the minimum gap height. Additionally, specific constructive characteristics of the fluid flow engine to be designed and/or specific technical requirements may be considered when determining the minimum gap height.
  • the rotor blades for the at least one circumferentially extending rotor blade row are manufactured according to the invention with such a length that the gap height of the gap between the tips of the rotor blades and the base of said slot equals the determined minimum gap height.
  • the above mentioned advantages connected with the method are correspondingly connected with the inventive fluid flow engine.
  • the rotor assembly may comprise two or more circumferentially extending rotor blade rows, each provided with a plurality of radially extending unshrouded rotor blades.
  • the number of slots of the engine casing is equal to the number of rotor blade rows.
  • a cross section of said slot is rectangular-shaped.
  • Figure 1 is a schematic illustration of a general arrangement of a gas turbine engine 10 having an inlet 12, a compressor 14, a combustor system 16, a turbine system 18, an exhaust duct 20 and a twin-shaft arrangement 22, 24.
  • the gas turbine engine 10 is generally arranged about an axis 26 which for rotating components is their rotational axis.
  • the arrangements 22, 24 may have the same or opposite directions of rotation.
  • the combustion system 16 comprises an annular array of combustor units, i.e. burner 36, only one of which is shown. In one example, there are six burners 36 evenly spaced about the engine 10.
  • the turbine system 18 includes a high-pressure turbine 28 drivingly connected to the compressor 14 by a first shaft 22 of the twin-shaft arrangement 22, 24.
  • the turbine system 18 also includes a low-pressure turbine 30 drivingly connected to a load (not shown) via a second shaft 24 of the twin-shaft arrangement.
  • axial is with respect to the axis 26.
  • upstream and downstream are with respect to the general direction of gas flow through the engine 10 and as seen in FIG.1 is generally from left to right.
  • the compressor 14 comprises an axial series of stator vanes and rotor blades mounted in a conventional manner.
  • the stator or compressor vanes may be fixed or have variable geometry to improve the airflow onto the downstream rotor or compressor blades.
  • Each turbine 28, 30 comprises an axial series of stator vanes and rotor blades mounted via rotor discs arranged and operating in a conventional manner.
  • a rotor assembly comprises an annular array of rotor blades or blades and the rotor disc.
  • air 32 is drawn into the engine 10 through the inlet 12 and into the compressor 14 where the successive stages of vanes and blades compress the air before delivering the compressed air into the combustion system 16.
  • a combustion chamber of the combustion system 16 the mixture of compressed air and fuel is ignited.
  • the resultant hot working gas flow is directed into, expands and drives the high-pressure turbine 28 which in turn drives the compressor 14 via the first shaft 22.
  • the hot working gas flow is directed into the low-pressure turbine 30 which drives the load via the second shaft 24.
  • the low-pressure turbine 30 can also be referred to as a power turbine and the second shaft 24 can also be referred to as a power shaft.
  • the load is typically an electrical machine for generating electricity or a mechanical machine such as a pump or a process compressor. Other known loads may be driven via the low-pressure turbine 30.
  • the fuel may be in gaseous and/or liquid form.
  • the turbine engine 10 shown and described with reference to FIG.1 is just one example of a number of engines or turbomachinery in which this invention can be incorporated.
  • Such engines can be gas turbines or steam turbine and include single, double and triple shaft engines applied in marine, industrial and aerospace sectors.
  • FIG. 2 shows a detail of a conventional fluid flow engine 1 in a schematic sectional view.
  • the fluid flow engine 1 comprises a stationary engine casing 2 and a rotor assembly 3 rotatable supported in the engine casing 2.
  • the rotor assembly 3 comprises at least one circumferentially extending rotor blade row 4 with a plurality of radially extending unshrouded rotor blades 5.
  • a gap 6 is provided between tips 7 of the rotor blades 5 and an inner surface 8 of the engine casing 2.
  • the gap 6 is required to prevent radial contact between the tips 7 and the inner surface 8 as far as possible.
  • the gap 6 has a minimum gap height H. This minimum gap height H can be determined to carry out the method according to the invention, i.e. to design an inventive fluid flow engine.
  • Figure 3 shows a detail of an embodiment of the inventive fluid flow engine 9 in a schematic sectional view.
  • the fluid flow engine 9 can be used as compressor for a gas turbine engine according to FIG.1 .
  • the fluid flow engine 9 comprises a stationary engine casing 38 and a rotor assembly 39 rotatable supported in the engine casing 38.
  • the rotor assembly 39 comprises at least one circumferentially extending rotor blade row 40 with a plurality of radially extending unshrouded rotor blades 41.
  • An inner surface 42 of the engine casing 38 comprises at least one circumferentially extending slot 43 arranged radially outside of the rotor blade row 40.
  • a gap 44 is provided between tips 45 of the rotor blades 41 and a base 46 of said slot 43.
  • a depth d of said slot 43 is less than the gap height H 1 of the gap 44.
  • the depth d of said slot 43 lies within a range of 50% to 95% of the gap height H 1 of the gap 44. Therefore, a gap 47 between the rotor blade tips 45 and the inner surface 42 without the slot 43 has a gap height h that is less than the gap height H 1 of the gap 44.
  • the gap height h lies within a range of 5% to 40% of the gap height H 1 of the gap 44.
  • the rotor blades 41 are longer than the conventional rotor blades according to FIG.2 about 50% to 95% of the gap height H 1 of the gap 44.
  • the gap height H 1 may be equal to the minimum gap height H of FIG.2 .
  • a cross section of said slot 43 is rectangular-shaped. Also the tips 45 of the rotor blades 41 are rectangular-shaped.
  • the width C T of the rotor blade tips 45 is less than the width of the slot 43, in particular the width of the base 46 of the slot 43.
  • a gap 50 is provided between a lateral surface 48 of the slot 43 and a lateral surface 49 of a rotor blade tip 45 .
  • the gap height c is equal to or less than 1% of the width C T of the rotor blade tips 45.
  • the invention is also applicable to guide vanes of a fluid flow engine arranged in a circumferentially extending row, wherein a slot is arranged radially inside of the row at an outer surface of a rotor hub.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15165253.4A 2015-04-27 2015-04-27 Procédé de conception d'un moteur à écoulement de fluide et moteur à écoulement de fluide Withdrawn EP3088672A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP15165253.4A EP3088672A1 (fr) 2015-04-27 2015-04-27 Procédé de conception d'un moteur à écoulement de fluide et moteur à écoulement de fluide
US15/563,285 US20180073381A1 (en) 2015-04-27 2016-03-30 Method for designing a fluid flow engine and fluid flow engine
EP16713423.8A EP3289183A1 (fr) 2015-04-27 2016-03-30 Procédé de conception d'un moteur d'écoulement de fluide, et moteur d'écoulement de fluide
PCT/EP2016/056963 WO2016173793A1 (fr) 2015-04-27 2016-03-30 Procédé de conception d'un moteur d'écoulement de fluide, et moteur d'écoulement de fluide
CN201680024609.XA CN107532478B (zh) 2015-04-27 2016-03-30 用于设计流体流发动机的方法和流体流发动机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15165253.4A EP3088672A1 (fr) 2015-04-27 2015-04-27 Procédé de conception d'un moteur à écoulement de fluide et moteur à écoulement de fluide

Publications (1)

Publication Number Publication Date
EP3088672A1 true EP3088672A1 (fr) 2016-11-02

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP15165253.4A Withdrawn EP3088672A1 (fr) 2015-04-27 2015-04-27 Procédé de conception d'un moteur à écoulement de fluide et moteur à écoulement de fluide
EP16713423.8A Withdrawn EP3289183A1 (fr) 2015-04-27 2016-03-30 Procédé de conception d'un moteur d'écoulement de fluide, et moteur d'écoulement de fluide

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP16713423.8A Withdrawn EP3289183A1 (fr) 2015-04-27 2016-03-30 Procédé de conception d'un moteur d'écoulement de fluide, et moteur d'écoulement de fluide

Country Status (4)

Country Link
US (1) US20180073381A1 (fr)
EP (2) EP3088672A1 (fr)
CN (1) CN107532478B (fr)
WO (1) WO2016173793A1 (fr)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4238170A (en) * 1978-06-26 1980-12-09 United Technologies Corporation Blade tip seal for an axial flow rotary machine
US4645417A (en) 1984-02-06 1987-02-24 General Electric Company Compressor casing recess
US4738586A (en) 1985-03-11 1988-04-19 United Technologies Corporation Compressor blade tip seal
GB2225388A (en) * 1988-10-01 1990-05-30 Rolls Royce Plc Rotor blade tip clearance setting in gas turbine engines
US6146089A (en) * 1998-11-23 2000-11-14 General Electric Company Fan containment structure having contoured shroud for optimized tip clearance
DE102004059904A1 (de) * 2004-12-13 2006-06-14 Alstom Technology Ltd Laufschaufel für eine Turbomaschine sowie Verfahren zu deren Herstellung
WO2011157927A1 (fr) * 2010-06-17 2011-12-22 Snecma Compresseur et turbomachine a rendement optimise.

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2231426C3 (de) * 1972-06-27 1974-11-28 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Deckbandlose, innen gekühlte Axialturbinenlaufschaufel
US4239452A (en) * 1978-06-26 1980-12-16 United Technologies Corporation Blade tip shroud for a compression stage of a gas turbine engine
US4606699A (en) * 1984-02-06 1986-08-19 General Electric Company Compressor casing recess
US8100640B2 (en) * 2007-10-25 2012-01-24 United Technologies Corporation Blade outer air seal with improved thermomechanical fatigue life
US8177494B2 (en) * 2009-03-15 2012-05-15 United Technologies Corporation Buried casing treatment strip for a gas turbine engine
US8562289B2 (en) * 2010-02-26 2013-10-22 Ge Aviation Systems, Llc Method and system for a leakage controlled fan housing

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4238170A (en) * 1978-06-26 1980-12-09 United Technologies Corporation Blade tip seal for an axial flow rotary machine
US4645417A (en) 1984-02-06 1987-02-24 General Electric Company Compressor casing recess
US4738586A (en) 1985-03-11 1988-04-19 United Technologies Corporation Compressor blade tip seal
GB2225388A (en) * 1988-10-01 1990-05-30 Rolls Royce Plc Rotor blade tip clearance setting in gas turbine engines
US6146089A (en) * 1998-11-23 2000-11-14 General Electric Company Fan containment structure having contoured shroud for optimized tip clearance
DE102004059904A1 (de) * 2004-12-13 2006-06-14 Alstom Technology Ltd Laufschaufel für eine Turbomaschine sowie Verfahren zu deren Herstellung
WO2011157927A1 (fr) * 2010-06-17 2011-12-22 Snecma Compresseur et turbomachine a rendement optimise.

Also Published As

Publication number Publication date
CN107532478A (zh) 2018-01-02
EP3289183A1 (fr) 2018-03-07
US20180073381A1 (en) 2018-03-15
CN107532478B (zh) 2020-02-21
WO2016173793A1 (fr) 2016-11-03

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