Gas turbine and method for varying the aerodynamic shape of a gas turbine blade

Inactive Publication Date: 2011-08-04
MTU AERO ENGINES GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Benefits of technology

[0009]The blades are preferably coated on the outer side with the shape-memory alloy. Naturally, as an option, the blade could also be coated on the inside, namely in that they are designed to be hollow on the inside.
[0010]According to the preferred embodiment, the coated blades are compressor blades, with which naturally the temperature is not as high as in the turbine region, whereby great temperature differences may be generated between the hot air feed and the hot air interrupt.
[0011]The channel or channels start in particular from a downstream compressor stage and direct hot air upstream fr

Problems solved by technology

However, this method for varying the aerodynamic shape of a blade is associated with very high electrical energy expenditures, because

Method used

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  • Gas turbine and method for varying the aerodynamic shape of a gas turbine blade
  • Gas turbine and method for varying the aerodynamic shape of a gas turbine blade

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DETAILED DESCRIPTION OF THE DRAWINGS

[0023]FIG. 1 depicts a gas turbine having an inlet diffuser 10, a compressor 12, a combustion chamber 14, a turbine 16 and a thrust nozzle 18, all of which are situated in a housing 20. Only by way of example, several of the numerous rotor blades 22 are depicted as part of the rotor and guide blades 24 are depicted as part of the stator in the compressor section or turbine section.

[0024]FIG. 2 shows that the depicted compressor 12 is multi-stage and has an axial design. It is easy to see that the guide blades 24 are connected to the housing 20 and the rotor blades 22 are connected to the rotor 26.

[0025]Directly upstream from the so-called blade tip 28 of a rotor blade ring, the housing 20 has several uniformly distributed blow-in openings 30 for hot gas on the circumference. The blow-in openings 30 are the end of one or more channels 32, which direct hot air upstream from a downstream compressor stage via one or more outlet openings 34. Arrow 36 s...

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Abstract

A gas turbine and a method for varying the aerodynamic shape of a blade of the gas turbine is disclosed. The blade has a coating made of a shape-memory alloy. Hot air is transported via channels to the coated blade in order to cause a phase change in the coating and an aerodynamic shape change to the blade.

Description

BACKGROUND AND SUMMARY OF THE INVENTION[0001]This application claims the priority of International Application No. PCT / DE2009 / 000997, filed Jul. 17, 2009, and German Patent Document No. 10 2008 033 783.8, filed Jul. 18, 2008, the disclosures of which are expressly incorporated by reference herein.[0002]The invention relates to a gas turbine having guide blades and rotor blades in the compressor section and turbine section.[0003]Gas turbines are used as aircraft propulsion devices in particular and have at least one rotor and at least one stator, and namely both in the compressor region as well as in the turbine region. The rotor blades assigned to the rotor rotate vis-à-vis the stationary housing and the likewise stationary guide blades.[0004]Gas turbines, particularly aircraft gas turbines, are subject to different ambient conditions and flow conditions, which they undergo during operation. Because of these different conditions, it is desirable to temporarily vary the geometric sha...

Claims

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Application Information

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IPC IPC(8): F01D5/18F01D5/14
CPCY02T50/673F01D5/141F01D5/148F04D29/023F05D2300/505F04D29/563F05D2230/90F05D2300/611F04D29/542Y02T50/60
Inventor HILLER, SVEN-J.
Owner MTU AERO ENGINES GMBH
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