Assembly of an axial turbomachine and method for manufacturing an assembly of this type

Patent metadata

Field	Value
Publication number	US-9366148-B2
Application number	US-201314013756-A
Country	US
Kind code	B2
Filing date	Aug 29, 2013
Priority date	Aug 30, 2012
Publication date	Jun 14, 2016
Grant date	Jun 14, 2016

Abstract

An assembly of an axial turbomachine includes at least one outlet guide vane of a compressor and a diffuser arranged downstream of the outlet guide vane in the flow direction. The outlet guide vane is connected to the compressor and the diffuser is connected to the combustion chamber, without there being a direct mechanical connection between the diffuser and the outlet guide vane.

First claim

The invention claimed is:

1. An assembly of an axial turbomachine, comprising:
a compressor;
a combustion chamber arranged downstream of the compressor in a flow direction:
at least one outlet guide vane of the compressor, the at least one outlet guide vane rotationally fixed with respect to the compressor and including a plurality of blades; and
a diffuser arranged downstream of the at least one outlet guide vane in the flow direction,
wherein the at least one outlet guide vane is connected to the compressor and the diffuser is connected to the combustion chamber, with no direct mechanical connection between the diffuser and the at least one outlet guide vane;
a leakage gap positioned between the at least one outlet guide vane and the diffuser in the flow direction;
wherein the at least one outlet guide vane is connected to an outer casing of the compressor.

2. The assembly in accordance with claim 1 , wherein the diffuser is connected to an inner combustion chamber casing of the combustion chamber.

3. The assembly in accordance with claim 1 , wherein the at least one outlet guide vane includes a hub gap extending between blade ends of the blades and a hub of the outlet guide vane.

4. The assembly in accordance with claim 3 , wherein the compressor includes a rotor arranged upstream of the outlet guide vane in the flow direction, the rotor including a rotor disk and a rotor hub, with the hub of the at least one outlet guide vane being separate from the blades of the at least one outlet guide vane and connected to at least one chosen from the rotor hub and the rotor disk.

5. The assembly in accordance with claim 3 , wherein the at least one outlet guide vane includes at least two outlet guide vanes provided in tandem arrangement behind one another in the flow direction, with each outlet guide vane forming a blade row and the blade rows of the at least two outlet guide vanes being fastened on one side to an outer casing of the compressor, wherein the compressor includes a rotor arranged upstream of the at least two outlet guide vanes in the flow direction, the rotor including a rotor disk and a rotor hub, with the hub of the at least two outlet guide vanes being separate from the blade rows of the at least two outlet guide vanes and connected to at least one chosen from the rotor hub and the rotor disk.

6. The assembly in accordance with claim 1 , wherein the at least one outlet guide vane includes a hub attached to ends of the blades such that the hub forms an integral part of the at least one outlet guide vane.

7. The assembly in accordance with claim 6 , and further comprising a shroud that at least partially closes a leakage gap between the at least one outlet guide vane and a rotor arranged upstream of the at least one outlet guide vane in the flow direction.

8. The assembly in accordance with claim 1 , wherein the at least one outlet guide vane includes at least two outlet guide vanes provided in tandem arrangement behind one another in the flow direction, with each of the at least two outlet guide vanes forming a blade row.

9. The assembly in accordance with claim 8 , wherein the at least two outlet guide vanes are separate parts bolted to one another.

10. The assembly in accordance with claim 8 , wherein at least one of the at least two out guide vanes is connected to the compressor, and at least one of the at least two outlet guide vanes is at least one chosen from connected to the diffuser and integral with the diffuser.

11. The assembly in accordance with claim 10 , and further comprising struts integrated into the diffuser for absorbing mechanical loads, with the at least two outlet guide vanes being connected to the diffuser.

12. The assembly in accordance with claim 1 , and further comprising struts integrated into the diffuser for absorbing mechanical loads.

13. The assembly in accordance with claim 12 , wherein the struts deflect an airflow through the diffuser.

14. The assembly in accordance with claim 1 , and further comprising a shroud that at least partially closes a leakage gap between the at least one outlet guide vane and a rotor arranged upstream of the at least one outlet guide vane in the flow direction.

15. A method for manufacturing an assembly of an axial turbomachine, comprising:
providing a compressor;
providing a combustion chamber arranged downstream of the compressor in a flow direction;
providing at least one outlet guide vane of the compressor, with the at least one outlet guide vane being rotationally fixed with respect to the compressor;
providing a diffuser arranged downstream of the at least one outlet guide vane in the flow direction;
separately manufacturing the at least one outlet guide vane and the diffuser,
connecting the at least one outlet guide vane to an outer casing of the compressor and connecting the diffuser to the combustion chamber, with no direct mechanical connection between the diffuser and the at least one outlet guide vane;
positioning a leakage gap between the at least one outlet guide vane and the diffuser in the flow direction.

16. The method in accordance with claim 15 , and further comprising manufacturing the at least one outlet guide vane by at least one chosen from electrical discharge machining (EDM), grinding, milling, sintering and electrochemical machining (ECM).

17. The method in accordance with claim 15 , and further comprising providing the diffuser as a casting.

18. The method in accordance with claim 15 , and further comprising providing a shroud that at least partially closes a leakage gap between the at least one outlet guide vane and a rotor arranged upstream of the at least one outlet guide vane in the flow direction.

Assignees

• Rolls Royce Deutschland

Inventors

• Clemen Carsten

Classifications

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F04D29/541

  Specially adapted for elastic fluid pumps (F04D29/56 takes precedence) · CPC title