High pressure compressor

• US 9,255,479 B2
• Filed: 12/05/2012
• Issued: 02/09/2016
• Est. Priority Date: 12/06/2011
• Status: Expired due to Fees

• Current Assignee: Ansaldo Energia IP UK Limited (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Pauli, Ernst, Shchukin, Sergey, Seng, Daniel
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US13/705,573
• Publication Number:
  US 20130170954A1
• Time in Patent Office: 1,161 Days
• Field of Search: 415115-116, 415175-177, 415/180, 416/95, 416/96.R, 416/97.R
• US Class Current: 1/1
• CPC Class Codes: F01D 5/08 Heating, heat-insulating or cooling means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/082 on the side of the rotor disc
• CPC Class Codes: F04D 29/053 Shafts
• CPC Class Codes: F04D 29/321 for axial flow compressors
• CPC Class Codes: F04D 29/584 cooling or heating the machine F04D29/5846, F04D29/5853 take precedence
• CPC Class Codes: F05B 2260/201 by impingement of a fluid
• CPC Class Codes: F05B 2260/2241 using fins or ribs
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

A high-pressure compressor (12), in particular in a gas turbine (10), has a compressor rotor (17) which is surrounded by a stator (18, 19) thereby forming a main flow channel (25) and which is delimited at the compressor outlet by an end face (30) substantially extending in the radial direction, along which end face cooling air (21) is conveyed in the radial direction for the purpose of cooling. A prolonged service life is achieved in that the end face (30) is provided with a first system (23, 24) for improving the heat transfer between the cooling air (21) and the end face (30).

Claims

1. A high-pressure compressor comprising:

a compressor rotor including a plurality of rotor disks being successively arranged in an axial direction, and a compressor stator surrounding the rotor thereby forming a main flow channel therebetween, the compressor stator including an outer stator part and an inner stator part;

a compressor outlet; and

a rotor end face on the last of said plurality of rotor disks at the compressor outlet extending in a radial direction, along which end face cooling air can be conveyed in the radial direction for cooling;

wherein the end face is surrounded by the inner stator part and faces in an axially downstream direction and includes first means for improving the heat transfer between the cooling air and the end face.

2. The high-pressure compressor according to claim 1, wherein the means for improving the heat transfer between the cooling air and the end face comprises, on the end face, a plurality of radially oriented blades which are circumferentially distributed and form cooling channels between each other for conveying the cooling air.

3. The high-pressure compressor according to claim 2, wherein the plurality of blades are molded onto the compressor rotor.

4. The high-pressure compressor according to claim 2, wherein each of the plurality of blades is formed curved counter to a rotational direction (ω

) of the compressor rotor.

5. The high-pressure compressor according to claim 4, wherein a curvature of each of the plurality of blades follows a parabola, a hyperbola, or a polynomial function.

6. The high-pressure compressor according to claim 1, comprising:

second means for imposing a tangential speed component in the rotational direction (ω

) of the compressor rotor onto the cooling air impinging onto said end face.

7. The high-pressure compressor according to claim 6, wherein:

the stator comprises an interior; and

the second means comprises a concentric turbulator nozzle which is arranged in the stator and through which cooling air exits from said stator interior and flows toward the end face.

8. The high-pressure compressor according to claim 7, wherein the turbulator nozzle comprises a group of blades.

9. The high-pressure compressor according to claim 7, wherein the turbulator nozzle comprises tangentially oriented boreholes.

10. The high-pressure compressor according to claim 1, further comprising:

a cooling cavity formed between the end face and the stator; and

a seal separating the cooling cavity from the main flow channel.

11. A gas turbine comprising a high-pressure compressor according to claim 1.