COMPRESSOR, METHOD AND TURBOMACHINE

• US 20170146025A1
• Filed: 11/22/2016
• Published: 05/25/2017
• Est. Priority Date: 11/24/2015
• Status: Active Grant

• Current Assignee: MTU Aero Engines AG (MTU)
• Original Assignee: MTU Aero Engines AG (MTU)
• Inventors: Schneider, Tim, ELORZA GOMEZ, Sergio
• Granted Patent: US 10,641,288 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 5/146 of blades with tandem configuration, split blades or slotted blades
• CPC Class Codes: F04D 19/00 Axial-flow pumps F04D21/00 takes precedence; pump comprising axial flow and radial flow stages F04D17/025
• CPC Class Codes: F04D 19/028 Layout of fluid flow through the stages
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/522 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/541 Specially adapted for elastic fluid pumps F04D29/56 takes precedence
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Described is a method for operating a compressor of a turbomachine, in which, when considered in the direction of a main flow, an, in particular, radially averaged degree of reaction has dropped in a front compressor area from a maximum to a minimum, is held constant or virtually constant across a central compressor area up into a rear compressor area, an, in particular, radially averaged degree of reaction being adjusted in the rear compressors area which is closer to the minimum than to the maximum, and a residual swirl of at least 47° is present in the middle section, and a compressor and a turbomachine.

Claims

1. A method for operating a compressor of a turbomachine, the method comprising:

dropping a radially averaged degree of reaction in a front compressor area, with respect to a main flow direction, from a maximum to a minimum;

holding the radially averaged degree of reaction substantially constant across a central compressor area up into a rear compressor area; and

adjusting the radially averaged degree of reaction in the rear compressor area to be closer to the minimum than to the maximum;

a residual swirl of at least 47°

being set in the middle section.

2. The method as recited in claim 1 wherein the radially averaged degree of reaction is adjusted to equal 0.5 or slightly higher.

3. The method as recited in claim 1 wherein a value of a local degree of reaction at half the radial height between a compressor hub and the compressor housing is reduced compared to an average value in the case of a linear radial curve.

4. A compressor of a turbomachine for carrying out the method as recited in claim 1.

5. The compressor as recited in claim 4 wherein the compressor has a hub-side or a housing-side sidewall contouring in the rear compressor area.

6. The compressor as recited in claim 4 wherein an outlet guide baffle is situated in a tandem form in the rear compressor area.

7. A turbomachine comprising the compressor as recited in claim 4.