Method for operating a compressor of a turbomachine comprising providing a plurality of stages in a front compressor area, a rear compressor area, and allowing a swirl in the rear compressor area

• US 10,641,288 B2
• Filed: 11/22/2016
• Issued: 05/05/2020
• 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
• Primary Examiner(s): Comley, Alexander B
• Assistant Examiner(s): Doyle, Benjamin
• Application Number:
  US15/359,113
• Publication Number:
  US 20170146025A1
• Time in Patent Office: 1,260 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:

providing a plurality of stages in a front compressor area so that a radially averaged degree of reaction in the front compressor area drops, with respect to a main flow direction, from a maximum at a first stage of the plurality of stages in the front compressor area to a front compressor area minimum at a further stage of the plurality of stages of the front compressor area downstream from the first stage;

providing a rear compressor area with a plurality of rear compressor area stages and an outlet guide baffle so that the radially averaged degree of reaction of the plurality of rear compressor area stages in the rear compressor area is closer to the front compressor area minimum than to the maximum; and

the rear compressor area allowing a swirl in the rear compressor area downstream from at least one of the plurality of rear compressor stages in front of the outlet guide baffle to be between 47° and

60°

in a middle section.

2. The method as recited in claim 1 wherein the degree of reaction is adjusted to equal 0.5 to 0.6.

3. The method as recited in claim 1 wherein a value of a local degree of reaction at half a radial height between a compressor hub and a compressor housing is less than each of a hub-side degree of reaction and a housing-side degree of reaction.

4. The method as recited in claim 1 wherein the front compressor area has a plurality of rows of adjustable guide blades, central compressor area between the front compressor area and the rear compressor area has a plurality of nonadjustable rows of guide blades, and rear compressor area has a plurality of rows of nonadjustable guide blades and a last row of guide blades defining the outlet guide baffle.

8. The method as recited in claim 1 wherein a value of a local degree of reaction at half a radial height between a compressor hub and a compressor housing is less than at least one of a hub-side degree of reaction and a housing-side degree of reaction.

5. A method for operating a compressor of a turbomachine, the compressor having a front compressor area having a plurality of rows of adjustable guide blades, a central compressor area having a plurality of nonadjustable rows of guide blades, and a rear compressor area having a plurality of rows of nonadjustable guide blades and a last row of guide blades defining an outlet guide baffle, the method comprising:

providing a plurality of stages in a front compressor area so that a radially averaged degree of reaction in the front compressor area drops, with respect to a main flow direction, from a maximum at a first stage of the plurality of stages in the front compressor area to a front compressor area minimum at a further stage of the plurality of stages of the front compressor area downstream from the first stage;

providing a rear compressor area with a plurality of rear compressor area stages and an outlet guide baffle so that the radially averaged degree of reaction of the plurality of rear compressor area stages in the rear compressor area is closer to the front compressor area minimum than to the maximum; and

the rear compressor area allowing a swirl angle in the rear compressor area downstream from at least one of the plurality of rear compressor stages in front of the outlet guide baffle to be between 50° and

60°

in a middle section.

6. The method as recited in claim 5 wherein the radially averaged degree of reaction is adjusted to equal 0.5 or higher.

7. The method as recited in claim 5 wherein a value of a local degree of reaction at half a radial height between a compressor hub and a compressor housing is less than each of a hub-side degree of reaction and a housing-side degree of reaction.