Stator component cooling

Patent metadata

Field	Value
Publication number	US-11230935-B2
Application number	US-201514857865-A
Country	US
Kind code	B2
Filing date	Sep 18, 2015
Priority date	Sep 18, 2015
Publication date	Jan 25, 2022
Grant date	Jan 25, 2022

Abstract

One aspect the present subject matter is directed to a nozzle segment including a stator component having an airfoil. The airfoil includes a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage within the radial cooling channel. The strut defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel and the plurality of film holes provide for bore cooling of the airfoil of at least one of the pressure side wall or the suction side wall and provide for film cooling of the trailing edge portion of the airfoil between about fifty percent and one hundred percent of the chord length.

First claim

What is claimed is:

1. A nozzle segment, comprising:
a stator component having an airfoil that extends radially between an inner band and an outer band, the stator component defining a radial cooling channel, the airfoil comprising a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel; and
a strut disposed within the radial cooling channel and defining an inner radial cooling passage within the radial cooling channel, the strut defining a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel;
wherein the plurality of apertures are positioned and arranged along one or more portions of the strut that are only within up to a first sixty percent of a chord length so as to provide impingement cooling to an inner surface of the airfoil, the chord length measured along a chord line from a starting point at the leading edge portion of the airfoil to a termination point at the trailing edge portion of the airfoil;
wherein the plurality of film holes provide for bore cooling of the airfoil of at least the suction side wall, wherein the plurality of film holes are positioned along the airfoil at a location only from forty percent along the chord length to up to eighty percent along the chord length, as measured along the chord line from the starting point at the leading edge portion of the airfoil;
wherein the plurality of film holes provide for film cooling of the trailing edge portion of the airfoil; and
wherein the trailing edge portion of the airfoil, including an interior of the trailing edge portion, is solid from a location corresponding to eighty percent of the chord length of the airfoil to the termination point at the trailing edge portion of the airfoil, as measured along the chord line from the starting point at the leading edge portion of the airfoil.

2. The nozzle segment as in claim 1 , wherein the stator component is formed from a ceramic matrix composite material.

3. The nozzle segment as in claim 1 , further comprising a baffle connected to the strut, wherein the baffle extends radially in span and chordwise about an aft portion of the strut and defines a flow passage between the baffle and the strut.

4. The nozzle segment as in claim 3 , wherein the flow passage of the baffle is in fluid communication with the inner radial cooling passage and the radial cooling channel.

5. The nozzle segment as in claim 3 , wherein the baffle defines a plurality of exhaust holes, wherein the plurality of exhaust holes provide for fluid communication from the flow passage through the baffle and into the radial cooling channel.

6. The nozzle segment as in claim 1 , further comprising a baffle connected to the strut so as to prevent direct impingement cooling of the inner surface of the airfoil aft of an aft portion of the strut.

7. The nozzle segment as in claim 6 , wherein the baffle extends radially in span from fifty percent to less than one-hundred percent of a total radial span of the strut.

8. The nozzle segment as in claim 7 , wherein the baffle provides fluid communication between the inner radial cooling passage and the radial cooling channel at a radially inward portion of the baffle and/or at a radially outward portion of the baffle.

9. A nozzle assembly, comprising:
a plurality of nozzle segments annularly arranged and coupled together via an outer support ring and an inner support ring, each nozzle segment comprising:
a stator component having an airfoil that extends radially between an inner band connected to the inner support ring and an outer band connected to the outer support ring, the stator component defining a radial cooling channel, the airfoil comprising a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel; and
a strut disposed within the radial cooling channel and defining an inner radial cooling passage within the radial cooling channel, the strut defining a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel;
wherein the plurality of apertures are positioned and arranged along one or more portions of the strut that are only within up to a first sixty percent of a chord length the strut so as to provide impingement cooling to an inner surface of the airfoil, the chord length measured along a chord line from a starting point at the leading edge portion of the airfoil to a termination point at the trailing edge portion of the airfoil;
wherein the plurality of film holes provide for bore cooling of the airfoil of at least the suction side wall, wherein the plurality of film holes are positioned along the airfoil at a location only from forty percent along the chord length to up to eighty percent along the chord length, as measured along the chord line from the starting point at the leading edge portion of the airfoil;
wherein the plurality of film holes provide for film cooling of the trailing edge portion of the airfoil from a location corresponding to fifty percent of the chord length to eighty percent of the chord length of the airfoil, as measured along the chord line from the starting point at the leading edge portion of the airfoil; and
wherein the trailing edge portion of the airfoil, including an interior of the trailing edge portion, is solid from a location corresponding to eighty percent of the chord length of the airfoil to the termination point at the trailing edge portion of the airfoil, as measured along the chord line from the starting point at the leading edge portion of the airfoil.

10. The nozzle assembly as in claim 9 , wherein the stator component is formed from a ceramic matrix composite material.

11. The nozzle assembly as in claim 9 , wherein each nozzle segment further comprises a baffle connected to the strut, wherein the baffle extends radially in span and chordwise about an aft portion of the strut and defines a flow passage between the baffle and the strut.

12. The nozzle assembly as in claim 11 , wherein the flow passage of the baffle is in fluid communication with the inner radial cooling passage and the radial cooling channel.

13. The nozzle assembly as in claim 11 , wherein the baffle defines a plurality of exhaust holes, wherein the plurality of exhaust holes provide for fluid communication from the flow passage through the baffle and into the radial cooling channel.

14. A gas turbine, comprising:
a compressor;
a combustor disposed downstream from the compressor; and
a turbine disposed downstream from the combustor, wherein the turbine comprises a nozzle assembly disposed upstream from a row of turbine blades, the nozzle assembly having a plurality of nozzle segments annularly arranged and coupled together via an outer support ring and an inner support ring, each nozzle segment comprising:
a stator component having an airfoil that extends radially between an inner band connected to the inner support ring and an outer band connected to the outer support ring, the stator component defining a radial cooling channel, the airfoil comprising a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel; and
a strut disposed within the radial cooling channel and defining an inner radial cooling passage within the radial cooling channel, the strut defining a plurality of apertures that pr

Assignees

• Gen Electric

Inventors

• Huizenga Benjamin Scott
• Senile Darrell Glenn
• Frederick Robert Alan
• Kreitzer Paul Joseph

Classifications

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/189

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title