EP2064427A1 - Cône d'entrée pour un moteur à réaction - Google Patents

Cône d'entrée pour un moteur à réaction

Info

Publication number
EP2064427A1
EP2064427A1 EP07801348A EP07801348A EP2064427A1 EP 2064427 A1 EP2064427 A1 EP 2064427A1 EP 07801348 A EP07801348 A EP 07801348A EP 07801348 A EP07801348 A EP 07801348A EP 2064427 A1 EP2064427 A1 EP 2064427A1
Authority
EP
European Patent Office
Prior art keywords
cone
region
inlet
solids
angle
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Withdrawn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
EP07801348A
Other languages
German (de)
English (en)
Inventor
Thomas Uihlein
Markus Uecker
Olivier Seite
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2064427A1 publication Critical patent/EP2064427A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical

Definitions

  • the present invention relates to an inlet cone for a jet engine designed as a turbofan engine, which has an engine core region and a jacket region surrounding it, wherein the inlet cone is arranged concentrically in the air inlet region of the jet engine and is arranged on a rotatably mounted shaft.
  • a generic cone arrangement is known from European Patent EP 0 294 654 Bl.
  • the outer shape of the cone arrangement corresponds to that of a paraboloid of revolution.
  • the wall of the cone arrangement is drawn inwardly to form a mounting flange, so that in the event of a foreign body impact on the cone assembly this remains undamaged due to a special design in the Anflansch Scheme to the rotor.
  • the trajectory of the foreign body which arrives at the cone arrangement can not be controlled.
  • a directional specification of the trajectory after rebounding from the cone arrangement is not possible.
  • An inlet cone 1 according to the prior art can be seen in the illustration in FIG. 4, which is arranged at the front end of a low-pressure turbine shaft 14 of a jet engine 10.
  • the jet engine 10 has an engine core region 11 and a jacket region 12.
  • the inlet cone 1 is arranged concentrically to the longitudinal axis 13 and has a shallow cone angle 15.
  • the flat or small cone angle 15 causes solid 16 striking the cone 1 to predominantly enter the engine core area 11 after it bounces off the surface of the cone 1.
  • the solids 16 move after rebounding from the cone 1 along various trajectories 17, the trajectories 17a in the engine core area and the trajectories 17b in drive the jacket area.
  • a majority of solids 16 are directed into the engine core region. This causes substantial damage to the engine core area 11, since the solids in the engine core area cause particularly severe erosion.
  • sulfates located in the sand and the associated sulfidation is one of the limiting damage mechanisms in low-pressure turbines.
  • the invention includes the technical teaching that the inlet cone is characterized by a cone angle, bounce in the impact with the air flow on the cone assembly solids in trajectories of the cone arrangement, which lead the solids predominantly in the cladding region.
  • the invention has the advantage that, by a suitably selected cone angle, the particle paths of the impinging solid are modified by modifying the impact angle and the air flow in particular over the entire cone arrangement in such a way that the impinging solids, such as sand particles, predominantly enter the shell region.
  • the impinging solids such as sand particles
  • the associated damage mechanisms are minimized. Due to a blunt inlet cone, less solid particles enter the engine core area than with a pointed cone. The Most particles thus get into the side stream, ie in the mantle area. There they can appear much less erosive and corrosive.
  • the cone angle of the cone arrangement has a value of 30 ° to 45 °, preferably of 35 ° to 40 ° and particularly preferably of 38 °.
  • an angle of about 38 ° as a half angle of the conical cone arrangement has been found to be particularly advantageous, since at this angle, only a very small proportion of the solids, which impinge on the cone assembly as a whole, enters the engine core area. Nevertheless, with a cone angle of 38 °, an ideal flow of the air flow which arrives in the jet engine is maintained.
  • the cone arrangement can be subdivided in the radial direction into an inner inflow region and into an outer inflow region, and the radial boundary between the regions is defined by a limiting flow radius.
  • the solids impinging upon the inner inflow region with the air flow reach the engine core region after rebounding from the cone arrangement via an inner trajectory and the solids impinging on the outer inflow region reach the jacket region after rebounding via an outer trajectory.
  • the Grenzströmradius in this case has a radius of 50% to 70%, preferably from 55% to 65%, and particularly preferably of 62% of the outer radius of the cone arrangement.
  • this extends over the entire length of the cone arrangement in the extension direction of the longitudinal axis with a uniform cone angle.
  • the outer side of the cone arrangement can pass without step into the area of the fan blades, so that an uninterrupted flow contour is formed.
  • the cone arrangement has a larger cone angle in the inner inflow region than in the outer inflow region, so that the angle bend of the different cone angles formed coincides with the limiting flow radius.
  • the cone arrangement according to this embodiment is designed such that it has a steep angle upstream, whereupon a flat cone angle follows in the flow direction, which merges into the blade arrangement.
  • the region in which the cone angle changes can advantageously fall within the boundary flow radius, so that the solids which impinge on the front steeper cone region are guided completely into the jacket region, whereupon only a small portion in the outer cone region adjoins the blade arrangement causes the solids to enter the engine core area.
  • cone arrangement can also be achieved a higher proportion of entering into the cladding region sand particles.
  • the present invention further relates to the use of a cone arrangement for a jet engine designed as a turbofan engine having an engine core region and a radially enveloping shell region, wherein the cone arrangement is arranged centrally in the air inlet region of the jet engine and is arranged at the front of the rotatable about a longitudinal axis low-pressure turbine shaft, and wherein the cone arrangement has a cone angle with a value of 30 ° to 45 °, preferably of 35 ° to 40 ° and particularly preferably of 38 °, wherein the solids impinging on the cone arrangement with the air stream bounces off the cone arrangement in trajectories, which the Lead solid mainly in the mantle area.
  • FIG. 1 shows an inlet cone of a jet engine with a cone angle according to the present invention.
  • Fig. 2 is a schematic representation of the cone and the
  • 3 is a schematic plan view of the inlet cone, which can be subdivided into an inner inflow region and an outer inflow region;
  • the inlet cone shown in FIG. 1 is provided with the reference number 1. This is located in the flow direction at the front of a jet engine 10 and is arranged concentrically with a longitudinal axis 13.
  • the inlet cone 1 is mounted on a low-pressure turbine shaft 14, so that the inlet cone 1 rotates with the turbine shaft.
  • the jet engine 10 can be subdivided into an inner engine core region 11 and an outer jacket region 12.
  • solid bodies 16 are shown which move along different movement paths 17.
  • the trajectories are divided into those which open into the engine core region 11, these are provided with the reference numeral 17a, wherein the trajectories 17, which open into the jacket region 12, are provided with the reference numeral 17b.
  • the solids 16 meet with the parallel to the longitudinal axis 13 extending flow of the air flow to the inlet cone 1. After impact, the solids 16 of cone 1 rebound and move along the illustrated trajectories 17a and 17b.
  • the cone 1 is formed with a cone angle 15, which has a value which is such that solid bodies 16 impinging on the air flow on the cone 1 follow the paths of movement 17b away from the cone 1, moving the solids 16 predominantly in lead the jacket area 12.
  • FIG. 2 schematically shows the arrangement of the cone and of the engine core region 11 and of the jacket region 12.
  • the longitudinal axis 13 is shown schematically as bisecting, so that the cone 1 extends relative to the longitudinal axis 13 at the cone angle 15.
  • the separation between the engine core region 11 and the jacket region 12 is shown schematically by a partition wall.
  • the solid 16 meet the entrance cone 1. After the rebound of the solid 16, these move along the inner and outer trajectories 17 a and 17 b.
  • the boundary between the inner Anström Society 18 and the outer Anström Scheme 19 is given by the Grenzströmradius 20, wherein the inner Anström Scheme 18 makes up the larger radius portion and only a smaller outer Anström Suite 19 is present.
  • FIG. 3 schematically illustrates a plan view of the inlet cone 1 from the direction of the longitudinal axis 13.
  • the limiting flow radius 20 defines the inner inflow region 18, whereas the outer inflow region 19 protrudes to the outer radius of the inlet cone 1.
  • the proportion of Grenzströmradius 20 in relation to the total radius of the cone assembly 1 is about 62%, so that only 38% of the incident on the proportionate radius solids arrive in the engine core area.
  • the present invention is not limited in its execution to the above-mentioned preferred Ausruhrungsbeispiel. Rather, a number of variants is conceivable, which makes use of the illustrated solution even with fundamentally different types of execution.
  • the cone 1 may also have a plurality of cone angle sections.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un cône d'entrée (1) pour un moteur à réaction (10) conçu en tant que réacteur à double flux, qui présente un secteur central de groupe moteur (11) et un secteur d'enveloppe (12) entourant celui-ci, le cône d'entrée (1) étant agencé de manière concentrique dans le secteur d'entrée d'air du moteur à réaction (10) et étant agencé au niveau d'un arbre (14) pivotant, le cône d'entrée (1) présentant un angle de cône (15), dans lequel des corps solides (16) impactant sur le cône d'entrée (1) avec le flux d'air rebondissent sur celui-ci selon des trajets de déplacement (17) qui conduisent les corps solides (16) principalement dans le secteur d'enveloppe (12). Un cône d'entrée (1) est ainsi créé, avec lequel l'entrée de corps solides (16) avec le secteur central de groupe moteur (11) peut être minimisée.
EP07801348A 2006-09-23 2007-09-18 Cône d'entrée pour un moteur à réaction Withdrawn EP2064427A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006044968A DE102006044968A1 (de) 2006-09-23 2006-09-23 Eintrittskonus für ein Strahltriebwerk
PCT/DE2007/001683 WO2008034425A1 (fr) 2006-09-23 2007-09-18 Cône d'entrée pour un moteur à réaction

Publications (1)

Publication Number Publication Date
EP2064427A1 true EP2064427A1 (fr) 2009-06-03

Family

ID=38857930

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07801348A Withdrawn EP2064427A1 (fr) 2006-09-23 2007-09-18 Cône d'entrée pour un moteur à réaction

Country Status (5)

Country Link
US (1) US20100119376A1 (fr)
EP (1) EP2064427A1 (fr)
CA (1) CA2664107A1 (fr)
DE (1) DE102006044968A1 (fr)
WO (1) WO2008034425A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202021104007U1 (de) 2021-07-27 2021-08-04 MTU Aero Engines AG Strahltriebwerk und Strahltriebwerksanordnung

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5182906A (en) * 1990-10-22 1993-02-02 General Electric Company Hybrid spinner nose configuration in a gas turbine engine having a bypass duct
DE102004018585B4 (de) * 2004-04-16 2013-12-05 Rolls-Royce Deutschland Ltd & Co Kg Triebwerkeinlaufkonus für ein Gasturbinentriebwerk
FR2873751B1 (fr) * 2004-07-28 2006-09-29 Snecma Moteurs Sa Cone d'entree d'une turbomachine
WO2006059987A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Séparateur de particules pour moteur à turbine en bout

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008034425A1 *

Also Published As

Publication number Publication date
CA2664107A1 (fr) 2008-03-27
US20100119376A1 (en) 2010-05-13
DE102006044968A1 (de) 2008-04-03
WO2008034425A1 (fr) 2008-03-27

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