Thermal Attenuation Structure For Detonation Combustion System

Patent metadata

Field	Value
Publication number	US-2019242582-A1
Application number	US-201815890637-A
Country	US
Kind code	A1
Filing date	Feb 7, 2018
Priority date	Feb 7, 2018
Publication date	Aug 8, 2019
Grant date	—

Abstract

A rotating detonation combustion (RDC) system including a detonation chamber wall extended along a longitudinal direction. The detonation chamber wall defines a detonation chamber radially in between the detonation chamber walls. The RDC system further includes a fuel-oxidizer nozzle defining a first convergent-divergent nozzle disposed upstream of the detonation chamber, and a gas nozzle defining a second convergent-divergent nozzle extended through the detonation chamber wall at least partially along the longitudinal direction. The gas nozzle provides a flow of gas into the detonation chamber at least partially co-directional to the detonation chamber wall.

First claim

What is claimed is:

1 . A rotating detonation combustion (RDC) system, the RDC system comprising:
a detonation chamber wall extended along a longitudinal direction, wherein the detonation chamber wall defines a detonation chamber radially inward thereof; a fuel-oxidizer nozzle defining a first convergent-divergent nozzle disposed upstream of the detonation chamber; and a gas nozzle defining a second convergent-divergent nozzle extended through the detonation chamber wall at least partially along the longitudinal direction, wherein the gas nozzle provides a flow of gas into the detonation chamber at least partially co-directional to the detonation chamber wall.

2 . The RDC system of claim 1 , wherein the gas nozzle is disposed between the fuel-oxidizer nozzle and the detonation chamber wall, and wherein the gas nozzle is disposed upstream of the detonation chamber.

3 . The RDC system of claim 1 , wherein the gas nozzle is defined through the detonation chamber wall at least partially along a radial direction relative to a combustion centerline.

4 . The RDC system of claim 1 , wherein the RDC system comprises a plurality of gas nozzle extended through the detonation chamber wall at least partially along a radial direction relative to a combustion centerline, wherein the plurality of gas nozzle are disposed in an adjacent circumferential arrangement through the detonation chamber wall relative to the combustion centerline.

5 . The RDC system of claim 4 , wherein the plurality of gas nozzle are further disposed in an adjacent arrangement along the longitudinal direction through the detonation chamber wall.

6 . The RDC system of claim 5 , wherein each longitudinal position of the plurality of gas nozzle defines an increasing pressure ratio along a downstream direction from the fuel-oxidizer nozzle, wherein the pressure ratio is relative to a pressure plenum and the detonation chamber.

7 . The RDC system of claim 1 , wherein the gas nozzle is disposed at an acute angle through the detonation chamber wall.

8 . The RDC system of claim 7 , wherein the detonation chamber wall defines a longitudinally extended portion within the detonation chamber, wherein the longitudinally extended portion is extended downstream of the gas nozzle to direct the flow of gas at least partially co-directional to the detonation chamber wall.

9 . The RDC system of claim 1 , wherein the gas nozzle is defined annularly around the combustion centerline.

10 . The RDC system of claim 1 , wherein the RDC system comprises a plurality of the gas nozzle disposed in an adjacent arrangement around a circumferential direction around the combustion centerline.

11 . A heat engine, comprising:
an inlet section through which a flow of oxidizer enters the heat engine; an expansion section through which a flow of combustion products exits the heat engine; and a rotating detonation combustion system disposed in serial arrangement between the inlet section and the expansion section, the RDC system comprising:
a detonation chamber wall extended along a longitudinal direction, wherein the detonation chamber wall defines a detonation chamber radially inward thereof;
a fuel-oxidizer nozzle defining a first convergent-divergent nozzle disposed upstream of the detonation chamber; and
a gas nozzle defining a second convergent-divergent nozzle extended through the detonation chamber wall at least partially along the longitudinal direction, wherein the gas nozzle provides a flow of gas into the detonation chamber at least partially co-directional to the detonation chamber wall.

12 . The heat engine of claim 11 , wherein the gas nozzle of the RDC system is disposed radially between the fuel-oxidizer nozzle and the detonation chamber wall, and wherein the gas nozzle is disposed upstream of the detonation chamber.

13 . The heat engine of claim 11 , wherein the gas nozzle of the RDC system is defined through the detonation chamber wall at least partially along a radial direction relative to a combustion centerline.

14 . The heat engine of claim 11 , wherein the RDC system comprises a plurality of gas nozzle extended through the detonation chamber wall at least partially along a radial direction relative to a combustion centerline, wherein the plurality of gas nozzle are disposed in an adjacent circumferential arrangement through the detonation chamber wall relative to the combustion centerline.

15 . The heat engine of claim 14 , wherein the plurality of gas nozzle are further disposed in an adjacent arrangement along the longitudinal direction through the detonation chamber wall.

16 . The heat engine of claim 15 , wherein each longitudinal position of the plurality of gas nozzle defines an increasing pressure ratio along a downstream direction from the fuel-oxidizer nozzle, wherein the pressure ratio is relative to a pressure plenum and the detonation chamber.

17 . The heat engine of claim 11 , wherein the gas nozzle of the RDC system is disposed at an acute angle through the detonation chamber wall.

18 . The heat engine of claim 17 , wherein the detonation chamber wall defines a longitudinally extended portion within the detonation chamber, wherein the longitudinally extended portion is extended downstream of the gas nozzle to direct the flow of gas at least partially co-directional to the detonation chamber wall.

19 . The heat engine of claim 11 , wherein the gas nozzle is defined annularly around the combustion centerline.

20 . The heat engine of claim 11 , wherein the RDC system comprises a plurality of the gas nozzle disposed in an adjacent arrangement around a circumferential direction around the combustion centerline.

Assignees

• Gen Electric

Inventors

• Johnson Arthur Wesley
• Vise Steven Clayton
• Cooper Clayton Stuart
• Zelina Joseph
• Pal Sibtosh

Classifications

• F23R7/00 Primary

  Intermittent or explosive combustion chambers · CPC title

• F02C5/11

  using valveless combustion chambers · CPC title

• F02C3/14

  characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/34

  Feeding into different combustion zones · CPC title