Injection systems for fuel and gas

Patent metadata

Field	Value
Publication number	US-2016169524-A1
Application number	US-201414567753-A
Country	US
Kind code	A1
Filing date	Dec 11, 2014
Priority date	Dec 11, 2014
Publication date	Jun 16, 2016
Grant date	—

Abstract

Embodiments of the present disclosure provide injection systems for fuel and air. According to one embodiment, an injection system can include a mixing zone embedded within a surface of a turbine nozzle and positioned between a first outlet and a second outlet, the turbine nozzle separating a combustor of a power generation system from a turbine stage of the power generation system, wherein the first outlet is oriented substantially in opposition to the second outlet; a first injection conduit for delivering a carrier gas to the mixing zone through the first outlet; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet; wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the first injection conduit and the second injection conduit.

First claim

1 . An injection system comprising:
a turbine nozzle positioned downstream of a combustor of a power generation system; a first injection conduit for delivering a carrier gas to a mixing zone through a first outlet; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet; wherein the mixing zone is embedded within a surface of the turbine nozzle and positioned between the first outlet and the second outlet, the first outlet being oriented substantially in opposition to the second outlet, and wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the first injection conduit and the second injection conduit.

2 . The injection system of claim 1 , wherein the mixing zone is embedded within a dimple of the surface of the turbine nozzle.

3 . The injection system of claim 1 , further comprising:
a mixing chamber embedded within the surface of the turbine nozzle and enclosing the mixing zone therein; and a discharge passage extending through the mixing chamber between the mixing zone and an exterior of the mixing chamber.

4 . The injection system of claim 3 , wherein a contour of the discharge passage prevents fluid communication of a combusted gas outside of the turbine nozzle into the mixing chamber.

5 . The injection system of claim 1 , wherein the combustor comprises a reheat combustor of the power generation system, and the surface of the turbine nozzle is exposed to a flow of fluid through the reheat combustor, wherein the power generation system comprises a gas turbine system.

6 . The injection system of claim 1 , wherein at least one of the first injection conduit and the second injection conduit is composed of a thermally conductive material, such that a respective fluid in one of the first injection conduit or the second injection conduit absorbs heat from the surface of the turbine nozzle.

7 . The injection system of claim 1 , further comprising a manifold embedded within the turbine nozzle, wherein the manifold is in fluid communication with the first injection conduit and a plurality of carrier gas feed conduits.

8 . An injection system comprising:
a turbine nozzle positioned downstream of a combustor of a power generation system; a first injection conduit for delivering a carrier gas to a surface of the turbine nozzle through a first outlet; at least one second injection conduit for delivering a fuel to the surface of the turbine nozzle through at least one second outlet, the at least one second injection conduit being positioned within the first injection conduit; and at least one barrier positioned between the first injection conduit and the at least one second injection conduit, wherein the at least one barrier separates the carrier gas in the first injection conduit from the fuel of the at least one second injection conduit.

9 . The injection system of claim 8 , wherein the at least one second injection conduit comprises a plurality of second injection conduits, and wherein each of the plurality of second injection conduits are positioned within the first injection conduit.

10 . The injection system of claim 9 , wherein the at least one barrier comprises a plurality of barriers, each of the plurality of barriers being positioned between the first injection conduit and a respective one of the plurality of second injection conduits, and wherein each of the plurality of barriers separates the fuel of each of the plurality of second injection conduits from the carrier gas of the first injection conduit.

11 . The injection system of claim 8 , further comprising a mixing chamber positioned within the surface of the turbine nozzle, wherein the carrier gas and the fuel intermix within the mixing chamber upon leaving the first injection conduit and the at least one second injection conduit.

12 . The injection system of claim 8 , wherein the first injection conduit is composed of a thermally conductive material, such that a respective fluid in one of the first injection conduit and the at least one second injection conduit absorbs heat from the surface of the turbine nozzle through the thermally conductive material.

13 . The injection system of claim 8 , wherein the surface of the turbine nozzle comprises one of a leading edge, a trailing edge, a suction surface, a pressure surface, and a sidewall of the turbine nozzle.

14 . An injection system comprising:
a turbine nozzle positioned downstream of a combustor of a power generation system; at least one first injection conduit for delivering one of a fuel and a carrier gas to a surface of the turbine nozzle through at least one first outlet; and at least two second injection conduits for delivering the other of the fuel and the carrier gas to the surface of the turbine nozzle through at least two second outlets, the at least two second outlets being adjacent to the at least one first outlet; wherein a linear arrangement of the at least one first outlet and the at least two second outlets forms an alternating sequence of outlets for the fuel and the carrier gas.

15 . (canceled)

16 . The injection system of claim 14 , further comprising a mixing zone positioned proximal to the surface of the turbine nozzle, wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the at least one first outlet and the at least two second outlets.

17 . The injection system of claim 14 , wherein the at least one first outlet and each of the at least two second outlets are substantially coplanar with each other.

18 . The injection system of claim 14 , wherein the surface of the turbine nozzle comprises one of a leading edge and a trailing edge of the turbine nozzle.

19 . The injection system of claim 14 , wherein each of the at least two second injection conduits is in thermal communication with the carrier gas.

20 . The injection system of claim 14 , wherein the surface of the turbine nozzle is exposed to a flow of fluid through the combustor of the power generation system, and wherein the power generation system comprises a gas turbine system.

21 . An injection system comprising:
a reheat combustor of a power generation system; a turbine nozzle positioned downstream of the reheat combustor; a first injection conduit for delivering a carrier gas to a mixing zone embedded within a surface of the turbine nozzle through a first outlet disposed on the surface of the turbine nozzle, the mixing zone being in fluid communication with a reaction chamber of the reheat combustor; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet disposed on the surface of the turbine nozzle, the second outlet being oriented substantially in opposition to the first outlet; wherein the mixing zone is positioned between the first outlet and the second outlet, and wherein the carrier gas and the fuel intermix within the mixing zone upon exiting the first outlet and the second outlet.

22 . An injection system comprising:
a reheat combustor of a power generation system; and a turbine nozzle positioned downstream of the reheat combustor, wherein the turbine nozzle includes:
a first injection conduit for delivering a carrier gas to a reaction zone of the reheat combustor through a first outlet disposed on a surface of the turbine nozzle,
at least one second injection conduit for delivering a fuel to the reaction zone of the reheat combustor through at least one second outlet, the at least one second in

Assignees

• Gen Electric

Inventors

• Widener Stanley Kevin
• Davis Jr Lewis Berkley
• Foster Gregory Thomas
• Graham Kaitlin Marie
• Venkataraman Krishnakumar

Classifications

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title

• F23R3/286 Primary

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

• F01D9/06

  Fluid supply conduits to nozzles or the like · CPC title

• F23R3/346 Primary

  for staged combustion · CPC title

• F23R2900/03341

  Sequential combustion chambers or burners · CPC title