EP2275690A2 - Compresseur axial - Google Patents

Compresseur axial Download PDF

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Publication number
EP2275690A2
EP2275690A2 EP10007329A EP10007329A EP2275690A2 EP 2275690 A2 EP2275690 A2 EP 2275690A2 EP 10007329 A EP10007329 A EP 10007329A EP 10007329 A EP10007329 A EP 10007329A EP 2275690 A2 EP2275690 A2 EP 2275690A2
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
rotor hub
compressor
height
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Withdrawn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
EP10007329A
Other languages
German (de)
English (en)
Other versions
EP2275690A3 (fr
Inventor
Carsten Clemen
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 Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2275690A2 publication Critical patent/EP2275690A2/fr
Publication of EP2275690A3 publication Critical patent/EP2275690A3/fr
Withdrawn legal-status Critical Current

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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
    • F04D29/26—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
    • F04D29/324—Blades
    • 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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade

Definitions

  • the invention relates to an axial compressor which comprises at least one rotor arranged in a housing with compressor blades extending from a rotor hub and a stator, in particular for an aircraft gas turbine.
  • the essential components of an axial compressor provided for increasing the pressure of the supplied air are the rotor which is rotatably driven in a housing and the guide means (stator) which is mounted on the housing inner wall and consists of individual guide vanes.
  • the rotor consists of compressor blades arranged at the circumference of a drive shaft or hub.
  • multi-stage compressors used in gas turbine engines comprise two or more connected to a drum and connected to a drive shaft rotor disks on the outer circumference of the compressor blades are either detachable and thus easily replaceable attached or - in the case of a blisk designed as a rotor - are integrally formed.
  • the compressor blades emanate directly from the outer peripheral surface of the rotor disk in a blisk
  • the compressor blades mounted axially or circumferentially on the rotor disk each have an integral blade root (platform, shroud) which is held on the rotor disk via a guide piece integrally formed on its underside is.
  • the transitional area between the compressor blades and the rotor hub that is, the compressor blade and the peripheral surface of the rotor disk with integrally molded blades and the blade root with interchangeable blades mounted on the rotor disk, however, experience secondary flow phenomena, for example, corner separations, channel vortices, or cross channel flows. which lead to flow separations on the blade surface and the rotor hub (blade root, rotor disk), in particular in rotors with high hub load such as the fan or the low-pressure compressor of a gas turbine engine, and result in locally high pressure losses. This reduces the compressor efficiency and consequently increases fuel consumption.
  • the invention is therefore based on the object of specifying a particular for aircraft gas turbines axial compressor with improved aerodynamic performance.
  • an axial compressor which comprises at least one arranged in a housing rotor with rotor hub starting compressor blades and a stator and the compressor blades a blade tip, a leading and trailing edge and a measured at the rotor hub chord length and measured at the blade center height between the rotor hub and Having blade tip
  • the core of the invention in the formation of an emanating from the trailing edge of the compressor blades and immediately adjacent to the rotor hub slot-shaped recess through which in the transition region between the rotor hub and compressor blades usually occurring secondary flows can be significantly reduced, and therefore caused by secondary flow phenomena losses can be reduced and thus the compressor efficiency is increased.
  • the rotor hub may be formed by the blade root of separately manufactured on the periphery of a rotor disk compressor blades or - in integrally connected to the rotor disk compressor blades - also directly through the rotor hub.
  • the slot-shaped recess has a maximum height of two percent of the blade height, which may be constant or different in the longitudinal direction of the recess, for example starting from the trailing edge may be gradually reduced.
  • the recess has a minimum length of ten percent of the chord length and a maximum length of 50 percent of the chord length.
  • the in Fig. 1 shown axial compressor which acts here as a low-pressure compressor in an aircraft gas turbine, comprises five rotors 2 connected to a rotor drum 1.
  • the rotor drum 1 is arranged in a housing 3 and connected to a drive shaft 4.
  • the Rotors 2 each consist of a rotor disk 5, which forms, as it were, a rotor hub 6 connected to the drive shaft 4, from the outer peripheral surface of which the compressor blades 7 originate.
  • the compressor blades 7 as detachably mounted on the rotor disk 5, exchangeable individual blades with a the outer peripheral surface of the rotor hub 6 and rotor disk 5 forming blade root 8 (inner shroud, inner platform) executed.
  • stator 9 Between the compressor blades 7 of the adjacent rotors 2 are each a stator 9, consisting of stator 3 attached to the housing 10 is arranged.
  • the compressor blades 7 can also be formed integrally on the rotor disks 5 (rotor hub 6) in the design of the rotors 2 as a blisk, so that in this case the compressor blades 7 emanate directly from the peripheral surface of the rotor disk 5 or rotor hub 6.
  • Fig. 2 schematically shows a directly from a hub 6, that is, the peripheral surface of the rotor disk 5 outgoing compressor blade 7, a blade tip 11, a leading edge 12 and a trailing edge 13 and a chord length C on the rotor hub 6 and a height H between the rotor hub 6 and blade tip eleventh at half the chord length C has.
  • a directly adjacent to the rotor hub 6 (rotor disk 5, blade root 8) section is formed from the rear edge 13 outgoing slot-shaped recess 14 in the compressor blade 7, whose height S does not exceed two percent of the blade height H and whose length L at least 10% of Chord length C and at most 50% of the chord length C is.
  • the height S of the recess 14 along the chord length C may be constant or variable.
  • the height S of the recess 14, which here has a length L of 10% of the chord length C gradually decreases towards the middle of the blade.
  • the formation of channel vortices, transverse flows and corner separations in the transition region between the rotor hub 6 - here the blade root 8 or the rotor disk 5 - becomes clear reduces and thus improves the secondary flow behavior and the flow to the subsequent stator 9, so that - especially in rotors with high hub load as the fan of a gas turbine engine - the rotor losses are reduced and increases the compressor efficiency and ultimately the fuel consumption can be reduced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10007329.5A 2009-07-17 2010-07-15 Compresseur axial Withdrawn EP2275690A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009033756A DE102009033756A1 (de) 2009-07-17 2009-07-17 Axialverdichter, insbesondere für eine Fluggasturbine

Publications (2)

Publication Number Publication Date
EP2275690A2 true EP2275690A2 (fr) 2011-01-19
EP2275690A3 EP2275690A3 (fr) 2017-04-26

Family

ID=42358034

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10007329.5A Withdrawn EP2275690A3 (fr) 2009-07-17 2010-07-15 Compresseur axial

Country Status (3)

Country Link
US (1) US20110027091A1 (fr)
EP (1) EP2275690A3 (fr)
DE (1) DE102009033756A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9359905B2 (en) 2012-02-27 2016-06-07 Solar Turbines Incorporated Turbine engine rotor blade groove
US10260524B2 (en) 2013-10-02 2019-04-16 United Technologies Corporation Gas turbine engine with compressor disk deflectors
GB201505400D0 (en) * 2015-03-30 2015-05-13 Rolls Royce Plc Multi coordinate reference system for positioning bladed drum
US12546223B2 (en) 2023-12-14 2026-02-10 Pratt & Whitney Canada Corp. Variable rim width turbine blade attachment

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Also Published As

Publication number Publication date
EP2275690A3 (fr) 2017-04-26
DE102009033756A1 (de) 2011-01-20
US20110027091A1 (en) 2011-02-03

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