Combustion chamber with double wall

Patent metadata

Field	Value
Publication number	US-10648667-B2
Application number	US-201615068100-A
Country	US
Kind code	B2
Filing date	Mar 11, 2016
Priority date	Mar 12, 2015
Publication date	May 12, 2020
Grant date	May 12, 2020

Abstract

A combustion chamber includes a duct wall for guiding a hot gas flow in a hot gas flow path during operation. The duct wall is a double-walled construction including an inner face, an outer face, and a wall cavity. A sleeve at least partly encloses the duct wall for guiding a cooling gas in a cooling channel between the sleeve and the duct wall along the outer surface of the duct wall to an exit end, and the cavity opens to the cooling channel. A gas turbine is disclosing as having such a combustion chamber.

First claim

The invention claimed is:

1. A combustion chamber, comprising:
a duct wall for guiding a hot gas flow in a hot gas flow path during operation, wherein the duct wall is a double-walled construction including an inner face, an outer face, and a plurality of wall cavities, each wall cavity extending from a cavity inlet to a cavity outlet along the duct wall; and
a sleeve at least partly enclosing the duct wall for guiding a cooling gas in a cooling channel between the sleeve and the duct wall along the outer face of the duct wall to an exit end, the cavity outlet of each wall cavity opening to the cooling channel,
wherein each wall cavity extends in a direction normal to an axial extension of the combustion chamber circumferentially around the duct wall from the cavity inlet to the cavity outlet, each wall cavity being separated from an adjacent wall cavity by a connecting piece which connects the outer face and the inner face,
wherein a first portion of the duct wall at a position along the axial extension of the combustion chamber is configured as a double wall which includes each wall cavity and a second portion of the duct wall at the position along the axial extension of the combustion chamber is configured as a single wall wherein the sleeve encloses the second portion and the sleeve does not enclose the first portion.

2. The combustion chamber according to claim 1 , wherein the sleeve comprises:
a plurality of apertures surrounding the duct wall, and spaced at a distance therefrom such that the cooling gas injected from a compressed gas plenum through the apertures during operation impinges on the duct wall and flows as cross flow towards the exit end of the cooling channel.

3. The combustion chamber according to claim 2 , wherein each cavity inlet is connected to the compressed gas plenum for impingement cooling of the duct wall.

4. The combustion chamber according to claim 2 , comprising:
wherein the plurality of wall cavities are specified for a specific cooling requirement, the combustion chamber being configured to include at least one additional aperture for additional impingement cooling when a limit temperature of a section of the duct wall is exceeded during a combustion chamber design test operation.

5. The combustion chamber according to claim 1 , wherein the duct wall has a rectangular, trapezoidal, elliptical, or circular cross section with a first cavity inlet on one side and a second cavity inlet on an opposite side and a first cavity outlet in a wall section connecting the first and second cavity inlet on one side of the hot gas flow and a second cavity outlet in a wall section connecting the first and second cavity inlet on an opposite side of the hot gas flow.

6. The combustion chamber according to claim 1 , wherein each cavity inlet and/or each cavity outlet is arranged next to a joint at which two sections of the duct wall are connected.

7. A gas turbine with at least one compressor, and at least one turbine, wherein the gas turbine comprises:
at least one combustion chamber according to claim 1 .

8. The gas turbine according to claim 7 , wherein the exit end of the cooling channel is connected to a burner of the gas turbine for introducing the cooling gas into the burner during operation.

9. The gas turbine according to claim 7 , wherein a plurality of the combustion chambers are circumferentially arranged around an axis of the gas turbine, and a section of the duct wall of two adjacent combustion chambers facing each other is configured as a double wall with each wall cavity, and each sleeve is arranged above a section of the duct wall facing towards the axis of the gas turbine.

10. The gas turbine according to claim 7 , wherein a plurality of the combustion chambers are circumferentially arranged around an axis of the gas turbine, each cavity inlet being arranged on a section of the duct wall of two adjacent combustion chambers facing each other, and each sleeve being arranged above a section of the duct wall facing towards the axis of the gas turbine.

11. The gas turbine according to claim 7 , wherein a plurality of the combustion chambers are circumferentially arranged around an axis of the gas turbine, and a section of the duct wall of two adjacent combustion chambers facing each other is configured as a double wall with the plurality of wall cavities, and each sleeve is arranged above a section of the duct wall facing away from the axis of the gas turbine.

12. The gas turbine according to claim 7 , wherein a plurality of the combustion chambers are circumferentially arranged around an axis of the gas turbine, each cavity inlet being arranged on a section of the duct wall of two adjacent combustion chambers facing each other, and each sleeve being arranged above a section of the duct wall facing away from the axis of the gas turbine.

13. A method for cooling the combustion chamber according to claim 1 , comprising:
feeding the cooling gas into each cavity inlet, through the plurality of wall cavities for cooling the duct wall; and
discharging the cooling gas into the cooling channel through each cavity outlet for further convective cooling of the duct wall.

14. The method for cooling the combustion chamber according to claim 13 , wherein the cooling gas is injected through a plurality of apertures surrounding the sleeve which is spaced at a distance from duct wall such that the cooling gas from a compressed gas plenum passing through the apertures, impinges on the duct wall, and flows as cross flow towards the exit end of the cooling channel.

15. The method for cooling the combustion chamber according to claim 14 , comprising:
feeding the cooling gas from the compressed gas plenum to the wall cavity through each cavity inlet and discharging the cooling gas to the cooling channel from each cavity outlet; and
injecting the cooling gas from the compressed gas plenum through the apertures, to impinge on the duct wall, and flow as the cross flow through the same cooling channel as the cooling gas which discharges from each cavity outlet.

16. The combustion chamber according to claim 1 , wherein the duct wall has each cavity inlet on one side and each cavity outlet on an opposite side with the each wall cavity extending from each cavity inlet on one side to each cavity outlet on the opposite side.

Assignees

• Ansaldo Energia Switzerland AG

Inventors

• Maurer Michael Thomas
• Baumgartner Felix

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23M5/08

  Cooling thereof; Tube walls · CPC title

• F23R2900/03043

  Convection cooled combustion chamber walls with means for guiding the cooling air flow · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title