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Low noise turbine for geared turbofan engine

a geared turbofan and low noise technology, applied in the direction of liquid fuel engines, machines/engines, efficient propulsion technologies, etc., can solve the problems of reducing aerodynamic efficiency, acoustically cutting-off designs may come at the expense of increased weight, and low pressure turbines can be significant noise sources

Inactive Publication Date: 2013-08-08
MTU AERO ENGINES GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent text describes a gas turbine engine with a low pressure turbine that operates at a high speed. The engine has a gear reduction between the low pressure turbine and the fan, and the number of blades in the low pressure turbine is selected to meet a formula that ensures the blades operate at a speed of 60,000 revolutions per minute. The engine produces 15,000 pounds of thrust or more and is designed to be highly efficient. The technical effect of this invention is to provide a gas turbine engine with improved performance and efficiency.

Problems solved by technology

The low pressure turbine can be a significant noise source, as noise is produced by fluid dynamic interaction between the blade rows and the vane rows.
However, acoustically cut-off designs may come at the expense of increased weight and reduced aerodynamic efficiency.

Method used

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  • Low noise turbine for geared turbofan engine
  • Low noise turbine for geared turbofan engine

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Embodiment Construction

[0031]FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include an augmentor section (not shown), or an intermediate spool, among other systems or features. The fan section 22 drives air along a bypass flowpath while the compressor section 24 drives air along a core flowpath for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures.

[0032]The engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted ...

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Abstract

A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.

Description

CROSS-REFERENCE TO RELATED APPLICATION[0001]This application is a continuation of U.S. patent application Ser. No. 13 / 403,005, filed Feb. 23, 2012, which claims priority to U.S. Provisional Application No. 61 / 592,643, filed Jan. 31, 2012.BACKGROUND[0002]This application relates to the design of a turbine which can be operated to produce noise that is less sensitive to human hearing.[0003]Gas turbine engines are known, and typically include a fan delivering air into a compressor. The air is compressed in the compressor and delivered downstream into a combustor section where it was mixed with fuel and ignited. Products of this combustion pass downstream over turbine rotors, driving the turbine rotors to rotate.[0004]Typically, there is a high pressure turbine rotor, and a low pressure turbine rotor. Each of the turbine rotors include a number of rows of turbine blades which rotate with the rotor. Interspersed between the rows of turbine blades are vanes.[0005]The low pressure turbine ...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/02
CPCF02C3/107F02K3/06F05D2260/961F05D2270/333F02C7/20Y02T50/671F04D29/056F02C7/06F01D5/02F02C3/04F04D29/26F05D2260/4031Y02T50/60
Inventor MORIN, BRUCE L.KORTE, DETLEF
Owner MTU AERO ENGINES GMBH
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