EP1738061A1 - Verfahren zur auslegung einer niederdruckturbine eines flugtriebwerks sowie niederdruckturbine - Google Patents
Verfahren zur auslegung einer niederdruckturbine eines flugtriebwerks sowie niederdruckturbineInfo
- Publication number
- EP1738061A1 EP1738061A1 EP05732126A EP05732126A EP1738061A1 EP 1738061 A1 EP1738061 A1 EP 1738061A1 EP 05732126 A EP05732126 A EP 05732126A EP 05732126 A EP05732126 A EP 05732126A EP 1738061 A1 EP1738061 A1 EP 1738061A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine
- blade
- stages
- mode
- limit
- 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.)
- Granted
Links
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
- F01D5/12—Blades
- F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
-
- 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
- F01D5/10—Anti- vibration means
-
- 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
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Definitions
- the invention relates to a turbine, in particular a low-pressure turbine, a gas turbine, in particular an aircraft engine, according to the preamble of patent claim 1.
- Gas turbines in particular aircraft engines, consist of several assemblies, namely among other things at least one compressor, preferably a low-pressure compressor and a high-pressure compressor, a combustion chamber and at least one turbine, in particular a high-pressure turbine and a low-pressure turbine.
- the compressors and the turbines of the aircraft engine preferably comprise several stages, which are positioned axially one behind the other in the direction of flow. Each stage is formed by a fixed guide vane ring and a rotating rotor blade ring, the fixed guide vane ring having a plurality of fixed guide vanes and the rotating rotor blade ring having a plurality of rotating rotor blades.
- Each of the stages is characterized by a parameter which indicates the ratio of the number of guide vanes to the number of rotor blades within the stage. This parameter is also known as the vane-to-blade ratio (V / B).
- the low pressure turbine of an aircraft engine in particular is a noise source that should not be neglected.
- the low-pressure turbine emits noise or noise, in particular, at frequencies that are an integral multiple of the so-called blade passing frequency (BPF).
- BPF blade passing frequency
- the so-called blade passing frequency of a stage is the frequency with which the rotating blades of the stage rotate past a fixed guide vane of the corresponding stage.
- the present invention is based on the problem of creating a new type of turbine, in particular a low-pressure turbine, a gas turbine, in particular an aircraft engine.
- a turbine in particular a low-pressure turbine, a gas turbine, in particular an aircraft engine, according to claim 1.
- the present invention specifies a construction principle or design principle for the stages of a turbine, namely a low-pressure turbine, of an aircraft engine.
- a low-pressure turbine comprises several stages, which are arranged axially one behind the other in the flow direction of the low-pressure turbine.
- Each stage is formed by a fixed guide vane ring and a rotating rotor blade ring.
- the guide vane ring has several fixed guide vanes, which are also known as Vanes.
- the rotating blade ring of each stage has several rotating blades, which are also known as blades.
- the present invention now specifies a construction principle or design principle with which the so-called vane-to-blade ratio of the stages of a low-pressure turbine can be adapted in such a way that the low-pressure turbine emits the lowest possible noise level or noise level, specifically in noise-critical operating conditions the turbine or the aircraft engine.
- noise-critical operating conditions are e.g. B. a landing approach of an aircraft or a taxiing of the aircraft on a tarmac of an airport.
- the noise emitted here is characterized by frequencies that are an integer multiple of the so-called blade passing frequency (BPF).
- FIG. 1 shows a diagram 10 for a low-pressure turbine with a total of seven stages, with six of the seven guide vane rings V2 to V7 and the seven rotor blade rings Bl to B7 being plotted on the horizontal axis of the diagram 10.
- the vane-to-blade ratio V / B is plotted on the vertical axis of the diagram 10.
- the reference number 17 in FIG. 1 indicates the design principle known from the prior art for designing the vane-to-blade ratio of low-pressure turbines.
- this is achieved by setting the vane-to-blade ratio V / B to a value of approximately 1.50 for these stages.
- V / B For the stages positioned upstream (V2 to B4), however, a vane-to-blade ratio is used according to the prior art V / B selected from about 0.90.
- such a vane-to-blade ratio lies within the range 15, so that according to the prior art there is no attenuation of sound waves with frequencies in the range of the blade passing frequency (BPF) in the upstream stages.
- reference number 17 shows the construction principle or design principle known from the prior art for the configuration of the vane-to-blade ratio for the stages of the low-pressure turbine.
- FIGS. 1 and 2 A particularly preferred design principle or construction principle for the vane-to-blade ratio for the stages of a low-pressure turbine is identified in FIGS. 1 and 2 by reference number 18. This is discussed in detail below.
- the vane-to-blade ratio is preferably between 0.6 and 0.8, in particular in a range of approximately 0.7.
- the vane-to-blade ratio V / B assumes a value in the range of the turbine stages arranged downstream, which is in a range between 1.3 and 1.5, preferably approximately 1.4 ,
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004016246A DE102004016246A1 (de) | 2004-04-02 | 2004-04-02 | Turbine, insbesondere Niederdruckturbine, einer Gasturbine, insbesondere eines Flugtriebwerks |
PCT/DE2005/000435 WO2005100750A1 (de) | 2004-04-02 | 2005-03-11 | Verfahren zur auslegung einer niederdruckturbine eines flugtriebwerks sowie niederdruckturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1738061A1 true EP1738061A1 (de) | 2007-01-03 |
EP1738061B1 EP1738061B1 (de) | 2012-05-02 |
Family
ID=34964490
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05732126A Expired - Fee Related EP1738061B1 (de) | 2004-04-02 | 2005-03-11 | Verfahren zur auslegung einer turbine eines flugtriebwerks |
Country Status (5)
Country | Link |
---|---|
US (1) | US7806651B2 (de) |
EP (1) | EP1738061B1 (de) |
DE (1) | DE102004016246A1 (de) |
ES (1) | ES2382382T3 (de) |
WO (1) | WO2005100750A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2918778A1 (de) | 2014-03-14 | 2015-09-16 | MTU Aero Engines GmbH | Verfahren zum auslegen einer turbine |
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-
2004
- 2004-04-02 DE DE102004016246A patent/DE102004016246A1/de not_active Ceased
-
2005
- 2005-03-11 US US11/547,581 patent/US7806651B2/en active Active
- 2005-03-11 EP EP05732126A patent/EP1738061B1/de not_active Expired - Fee Related
- 2005-03-11 WO PCT/DE2005/000435 patent/WO2005100750A1/de active Application Filing
- 2005-03-11 ES ES05732126T patent/ES2382382T3/es active Active
Non-Patent Citations (1)
Title |
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See references of WO2005100750A1 * |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2918778A1 (de) | 2014-03-14 | 2015-09-16 | MTU Aero Engines GmbH | Verfahren zum auslegen einer turbine |
US10066486B2 (en) | 2014-03-14 | 2018-09-04 | MTU Aero Engines AG | Method for designing a turbine |
Also Published As
Publication number | Publication date |
---|---|
US7806651B2 (en) | 2010-10-05 |
DE102004016246A1 (de) | 2005-10-20 |
WO2005100750A1 (de) | 2005-10-27 |
US20080022691A1 (en) | 2008-01-31 |
ES2382382T3 (es) | 2012-06-07 |
EP1738061B1 (de) | 2012-05-02 |
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