Finely distributed combustion system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11248795-B2
Application number	US-201815733516-A
Country	US
Kind code	B2
Filing date	Mar 9, 2018
Priority date	Mar 9, 2018
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

A finely distributed combustion system for a gas turbine engine is provided. A combustor body may extend along a longitudinal axis. A premixer space may be formed within the combustor body to premix air and fuel. The premixer space is in communication with an array of finely distributed perforations arranged in a wall of the combustor body to eject an array of premixed main flamelets throughout a contour of the combustor body between the upstream base of the combustor body and the downstream base of the combustor body. The array of finely distributed perforations—potentially comprising thousands or even hundreds of thousands of perforations spatially distributed on a miniaturized scale—for ejecting the premixed main flamelets is technically advantageous compared to conventional distributed combustion systems, where injection of relatively longer main flames occurs just at a few discrete axial locations.

First claim

What is claimed is:

1. A finely distributed combustion system for a gas turbine engine, the finely distributed combustion system comprising:
a plurality of combustor towers extending along a longitudinal axis of the finely distributed combustion system between an upstream base of the plurality of combustor towers and a downstream base of the plurality of combustor towers,
wherein each combustor tower of the plurality of combustor towers comprises a wall, which defines an array of finely distributed perforations, extending between the upstream base and the downstream base,
wherein each combustor tower of the plurality of combustor towers comprises a hollow triangular prism interior which defines a respective enclosed premixer space to premix air and fuel,
wherein the plurality of combustor towers are circumferentially arranged around a central channel located along the longitudinal axis and are enclosed by a liner structure, and
wherein the array of finely distributed perforations is configured to eject an array of premixed main flamelets from the respective enclosed premixer space to the central channel.

2. The finely distributed combustion system of claim 1 , wherein the upstream base comprises an open base to receive a flow of air conveyed to the respective enclosed premixer space.

3. The finely distributed combustion system of claim 2 , further comprising respective main fuel-conveying conduits constructed within the wall, wherein at least one of the respective main fuel-conveying conduits is in fluid communication with the respective enclosed premixer space.

4. The finely distributed combustion system of claim 1 , wherein at least a portion of the wall comprises an array of finely distributed diffusion pilot perforations arranged to eject diffusion pilot flamelets interspersed with at least some of the array of premixed main flamelets for performing loading of the gas turbine engine.

5. The finely distributed combustion system of claim 4 , further comprising respective pilot fuel-conveying conduits constructed within the wall, wherein at least one of the respective pilot fuel-conveying conduits is in fluid communication with one or more of respective diffusion pilot perforations of the array of finely distributed diffusion pilot perforations.

6. The finely distributed combustion system of claim 1 , further comprising a fuel lance within at least one combustor tower of the plurality of combustor towers, the fuel lance comprising fuel ejection orifices arranged along the longitudinal axis of the finely distributed combustion system between the upstream base and the downstream base.

7. The finely distributed combustion system of claim 1 , wherein a respective perforation of the array of finely distributed perforations comprises a diameter in a range from 0.5 mm to 4 mm.

8. The finely distributed combustion system of claim 1 , wherein the wall where a respective perforation of the array of finely distributed perforations is constructed comprises a wall thickness in a range from 4 mm to 20 mm.

9. The finely distributed combustion system of claim 1 , wherein a respective perforation of the array of finely distributed perforations comprises a centrally-arranged perforation relative to a neighboring group of perforations in the array of finely distributed perforations, wherein the neighboring group of perforations defines a hexagonal arrangement.

10. The finely distributed combustion system of claim 9 , wherein a center-to-center distance between the centrally-arranged perforation and each of the neighboring group of perforations comprises a range from 1.5 d to 4 d, where d comprises a diameter of a perforation of the neighboring group of perforations.

11. The finely distributed combustion system of claim 1 , wherein the hollow triangular prism interior is filled with a porous metal media and comprises respective finely distributed perforations of the array of finely distributed perforations.

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• North Andrew J
• Portillo Bilbao Juan Enrique
• Laster Walter Ray
• Chen Yuntao

Classifications

• F23R2900/00008

  Combustion techniques using plasma gas · CPC title

• F23D2203/104

  Grids, e.g. honeycomb grids · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23D14/62

  Mixing devices; Mixing tubes · CPC title