EP1703081A1 - Seitenplatte - Google Patents

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Publication number
EP1703081A1
EP1703081A1 EP06250365A EP06250365A EP1703081A1 EP 1703081 A1 EP1703081 A1 EP 1703081A1 EP 06250365 A EP06250365 A EP 06250365A EP 06250365 A EP06250365 A EP 06250365A EP 1703081 A1 EP1703081 A1 EP 1703081A1
Authority
EP
European Patent Office
Prior art keywords
lock plate
lock
plate
flow
chute
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Withdrawn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
EP06250365A
Other languages
English (en)
French (fr)
Inventor
Jeffrey Alison Dixon
Ivan Lars Brunton
Timothy John Scanlon
Guy David Snowsill
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP1703081A1 publication Critical patent/EP1703081A1/de
Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades

Definitions

  • a gas turbine engine is generally indicated at 10 and comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, combustion equipment 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18 and an exhaust nozzle 19.
  • the compressed air exhausted from the high pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 16, 17 and 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low pressure turbine 16, 17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13, and the fan 12 by suitable interconnecting shafts.
  • turbine blades require appropriate mounting in order to allow rotation for operational performance in creating a propulsive axial gas flow, but also that the blades must be appropriately cooled. It will be understood that turbine engine efficiency is closely related to operational temperatures and that acceptable operational temperatures are dictated to a significant extent by the material properties of the components. In such circumstances by appropriate cooling it is possible to operate these components near to and occasionally exceeding the melting points for the materials for which they are constructed.
  • coolant air is taken from the compressor stages of a gas turbine engine.
  • this drainage of compressed coolant air reduces engine efficiency.
  • there are relatively intricate coolant passageways provided within the engine components which are arranged to provide cooling as the coolant passes through these passages as well as provide generally nozzle projection of the coolant flows where required into cavities in order to create turbulence with hot gas flows for a cooling diluted effect.
  • Fig. 2 illustrates a schematic cross-section of a prior cooling arrangement as a schematic cross-section.
  • a blade root 1 forms a shank with a locking plate 2 presented across the root 3 of the blade.
  • seals 4 are provided in the form of a labyrinth seal arrangement with coolant airflow in the direction of arrowhead 5 presented upwardly into the cavity 6 formed between the mounting disc 7 for the blade 1 and the bottom of a nozzle vane defining the turbine stages.
  • gap 8 through which hot gas is ingested to the cavity 6.
  • cooling air leakage flow 9 generally creates a barrier layer around the surfaces of the cavity 6 particularly on the rotor surface.
  • the coolant air 5 has been arranged to prevent excessive hot gas ingestion 8.
  • US 629464 describes provision of an outlet nozzle in order to project coolant flow through the fir tree root coolant passages into such a cavity in order to create turbulence and therefore cooling within that cavity. Such an approach does not utilise the boundary layer created by the lock plate leakage to protect the disc rim from ingestion of hot gas through the gap.
  • a lock plate for a blade mounting assembly within a gas turbine engine, the lock plate integrally shaped to form a chute for direct outward marginal flow across the lock plate for presentation of a coolant flow substantially in alignment with the lock plate.
  • the chute is formed in an end of the lock plate.
  • the chute is formed intermediately between ends of the lock plate.
  • the chute is formed by a passage shaped within the width of the lock plate.
  • a plate mounting arrangement for a gas turbine engine comprising a lock plate associated with a mounting disc for a plurality of turbine blades, the lock plate defined as above.
  • chutes 39 act to direct the leakage flow 32 effectively adjacent to the lock plates 28, 29 both in terms of release of that flow 32 as well as protecting the rotor surfaces 33, 34 from the hot gas ingestion 35.
  • chutes 39 will be formed towards a rear end of the lock plates 28, 29 that is to say downstream of the rotation direction 25 for the arrangement. However, as will be described later, chutes may be formed between the ends of the lock plates as required by operational performance.
  • a lock plate 50 is associated with a lock plate 51 such that respective ends abut each other at a joint 52. As indicated previously this joint is not perfect and therefore in use will tend to leak a coolant flow as described in Figure 1 by reference to arrowheads 32.
  • Chutes 59 are provided at the ends of the lock plates 50, 51 generally downstream of the direction of rotation (arrowhead 55).
  • the chutes 59 are formed such that a ramp effect is created to divert the ingested hot flow as described previously and provide an opening or aperture 53 for presentation of the coolant airflow 32 ( Figure 3).
  • the chutes 59 are integral with the lock plates 50, 51 and as indicated above are generally formed during a moulding or casting process.
  • Figure 6 provides a schematic plan view of the junction 52 between lock plates 50 and 51.
  • the chute 59 extends outwardly along the aperture 53 through which the coolant air flow 132 passes. It will be noted that this flow 132 remains relatively close to a wall surface 56 for cooling efficiency. As described previously, ingested hot gas flow 135 passes over the chute 59 and constrains the flow 132 as a barrier layer adjacent to the surface 56 again to facilitate cooling efficiency.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06250365A 2005-02-23 2006-01-24 Seitenplatte Withdrawn EP1703081A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB0503676.9A GB0503676D0 (en) 2005-02-23 2005-02-23 A lock plate arrangement

Publications (1)

Publication Number Publication Date
EP1703081A1 true EP1703081A1 (de) 2006-09-20

Family

ID=34401145

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06250365A Withdrawn EP1703081A1 (de) 2005-02-23 2006-01-24 Seitenplatte

Country Status (3)

Country Link
US (1) US20060188377A1 (de)
EP (1) EP1703081A1 (de)
GB (1) GB0503676D0 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2009244A1 (de) * 2007-06-27 2008-12-31 Snecma Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9803485B2 (en) 2013-03-05 2017-10-31 Rolls-Royce North American Technologies, Inc. Turbine segmented cover plate retention method
DE102016107315A1 (de) 2016-04-20 2017-10-26 Rolls-Royce Deutschland Ltd & Co Kg Rotor mit Überhang an Laufschaufeln für ein Sicherungselement
EP3810900A1 (de) * 2018-07-23 2021-04-28 Siemens Energy Global GmbH & Co. KG Abdeckplatte mit strömungsinduktor und verfahren zur kühlung von turbinenschaufeln
CN114562339B (zh) * 2022-01-27 2024-01-16 西北工业大学 一种用于涡轮端壁带凸起的泄漏槽气膜冷却结构及应用

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US629464A (en) 1899-02-18 1899-07-25 Robert M Paul Outlet-valve for water-tanks.
FR1426933A (fr) * 1964-08-05 1966-02-04 Gen Electric Perfectionnements aux rotors de turbomachines
GB1209419A (en) * 1968-06-24 1970-10-21 Westinghouse Electric Corp Side plates for turbine blades
EP0916808A2 (de) * 1997-11-05 1999-05-19 Rolls-Royce Plc Turbine
US5941687A (en) * 1996-11-12 1999-08-24 Rolls-Royce Plc Gas turbine engine turbine system
US6290464B1 (en) 1998-11-27 2001-09-18 Bmw Rolls-Royce Gmbh Turbomachine rotor blade and disk
US6416282B1 (en) * 1999-10-18 2002-07-09 Alstom Rotor for a gas turbine
EP1284338A2 (de) * 2001-08-13 2003-02-19 General Electric Company Kühleinsatz mit tangentialer Ausströmung

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4279572A (en) * 1979-07-09 1981-07-21 United Technologies Corporation Sideplates for rotor disk and rotor blades
DE3736836A1 (de) * 1987-10-30 1989-05-11 Bbc Brown Boveri & Cie Axial durchstroemte gasturbine
US4890981A (en) * 1988-12-30 1990-01-02 General Electric Company Boltless rotor blade retainer
US5755556A (en) * 1996-05-17 1998-05-26 Westinghouse Electric Corporation Turbomachine rotor with improved cooling
DE69830026T2 (de) * 1997-07-11 2005-09-29 Rolls-Royce Plc Schmierung einer Gasturbine während des Starts

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US629464A (en) 1899-02-18 1899-07-25 Robert M Paul Outlet-valve for water-tanks.
FR1426933A (fr) * 1964-08-05 1966-02-04 Gen Electric Perfectionnements aux rotors de turbomachines
GB1209419A (en) * 1968-06-24 1970-10-21 Westinghouse Electric Corp Side plates for turbine blades
US5941687A (en) * 1996-11-12 1999-08-24 Rolls-Royce Plc Gas turbine engine turbine system
EP0916808A2 (de) * 1997-11-05 1999-05-19 Rolls-Royce Plc Turbine
US6290464B1 (en) 1998-11-27 2001-09-18 Bmw Rolls-Royce Gmbh Turbomachine rotor blade and disk
US6416282B1 (en) * 1999-10-18 2002-07-09 Alstom Rotor for a gas turbine
EP1284338A2 (de) * 2001-08-13 2003-02-19 General Electric Company Kühleinsatz mit tangentialer Ausströmung

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2009244A1 (de) * 2007-06-27 2008-12-31 Snecma Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind
FR2918106A1 (fr) * 2007-06-27 2009-01-02 Snecma Sa Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine.
US8348620B2 (en) 2007-06-27 2013-01-08 Snecma Device for axially retaining blades mounted on a turbomachine rotor disk
RU2471999C2 (ru) * 2007-06-27 2013-01-10 Снекма Устройство для аксиального удержания лопаток, установленных на роторном диске газотурбинного двигателя

Also Published As

Publication number Publication date
GB0503676D0 (en) 2005-03-30
US20060188377A1 (en) 2006-08-24

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