Method for manufacturing a burner assembly for a gas turbine combustor and burner assembly for a gas turbine combustor

Patent metadata

Field	Value
Publication number	US-2018231254-A1
Application number	US-201815894342-A
Country	US
Kind code	A1
Filing date	Feb 12, 2018
Priority date	Feb 13, 2017
Publication date	Aug 16, 2018
Grant date	—

Abstract

A method for manufacturing a burner assembly for a gas turbine combustor, having a pilot burner extending along a longitudinal axis, and a premix burner surrounding the pilot burner, wherein the method includes manufacturing at least one portion of the pilot burner by an additive manufacturing technique which includes manufacturing at least one first thermal bridge connecting parts of the pilot burner having a temperature difference not greater than a threshold value.

First claim

1 . Method for manufacturing a burner assembly for a gas turbine combustor the burner assembly having a pilot burner extending along a longitudinal axis (A) and a premix burner surrounding the pilot burner, the method comprising:
manufacturing at least one portion of the pilot burner by an additive manufacturing technique which includes manufacturing at least one first thermal bridge connecting parts of the pilot burner; and wherein a temperature difference (ΔT) between said parts of the pilot burner is lower than a threshold value.

2 . Method according to claim 1 , wherein the parts of the pilot burner connected by the first thermal bridge are distinct elements of the pilot burner.

3 . Method according to claim 1 , wherein manufacturing at least one portion of the pilot burner comprises:
manufacturing a lance which is configured with an end tip, having a first conduit arranged to be supplied, in use, with a first fuel, and with a second conduit arranged to be supplied, in use, with air.

4 . Method according to claim 3 , wherein the first thermal bridge connects at least one wall of the first conduit configured for a temperature of a first fuel with a wall of the second conduit configured for air temperature.

5 . Method according to claim 4 , wherein the first thermal bridge is hollow so as to create a channel for passage of a fluid.

6 . Method according to claim 3 , wherein manufacturing at least one portion of the pilot burner comprises:
manufacturing a third conduit of the lance arranged to be supplied, in use, with a second fuel, and at least one second thermal bridge connecting at least one wall of the third conduit configured for a temperature of the second fuel with a wall of the first conduit configured for the temperature of the first fuel.

7 . Method according to claim 3 , wherein manufacturing at least one portion of the pilot burner comprises:
manufacturing at least one third thermal bridge connecting at least one wall of the second conduit configured for air temperature with a wall of the end tip configured for a temperature of an interior of the combustor.

8 . Method according to claim 1 , wherein manufacturing at least one portion of the pilot burner comprises:
determining three dimensional information of the portion of the pilot burner to be manufactured; converting the three dimensional information into a plurality of cross sectional layers; forming a support structure having a support portion laying on a base plate and an excess portion laying on the support portion; forming the portion of the pilot burner by adding each cross sectional layer previously defined on a support structure; and cutting away the support structure.

9 . Method according to claim 8 , wherein said forming the support structure comprises:
forming the excess portion by adding at least one excess layer on the support portion, the excess layer being identical to a first cross sectional layer to be added on the support structure.

10 . Burner assembly for a gas turbine combustor, the burner comprising:
a pilot burner extending along a longitudinal axis (A); and a premix burner surrounding the pilot burner the pilot burner having at least one first thermal bridge connecting parts of the pilot burner; wherein a temperature difference (ΔT) between said parts of the pilot burner is lower than a threshold value.

11 . Burner assembly according to claim 10 , wherein the parts of the pilot burner connected by the first thermal bridge are distinct elements of the pilot burner.

12 . Burner assembly according to claim 10 , wherein the pilot burner comprises:
a lance which is configured with an end tip, having a first conduit arranged to be supplied, in use, with a first fuel, and with a second conduit arranged to be supplied, in use, with air.

13 . Burner assembly according to claim 12 , wherein the first thermal bridge connects at least one wall of the first conduit configured for a temperature of a first fuel with a wall of the second conduit configured for air temperature.

14 . Burner assembly according to claim 12 , wherein the pilot burner comprises:
a third conduit arranged to be supplied, in use, with a second fuel and at least one second thermal bridge connecting at least one wall of the third conduit configured for a temperature of a second fuel with a wall of the first conduit configured for the temperature of the first fuel.

15 . Burner assembly according to claim 12 , wherein the pilot burner comprises:
at least one third thermal bridge connecting at least one wall of the second conduit configured for the temperature of the first fuel with a wall of the end tip configured for a temperature of an interior of the combustor.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Maurer Michael
• Gaupp Christoph

Classifications

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• B22F10/66

  by mechanical means · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B22F10/40

  Structures for supporting workpieces or articles during manufacture and removed afterwards · CPC title

• F23R3/36

  Supply of different fuels · CPC title