Combustor nozzle, gas turbine combustor, gas turbine, cover ring, and combustor nozzle manufacturing method

Patent metadata

Field	Value
Publication number	US-10837642-B2
Application number	US-201615738200-A
Country	US
Kind code	B2
Filing date	Jun 8, 2016
Priority date	Jul 3, 2015
Publication date	Nov 17, 2020
Grant date	Nov 17, 2020

Abstract

Provided are a combustor nozzle, a gas turbine combustor, a gas turbine, a cover ring, and a combustor nozzle manufacturing method. The combustor nozzle includes: a nozzle body provided with a fuel flow passage; a cover ring that is disposed on an outer side of the nozzle body so as to form air flow passages that allow air to jet out toward a front side; and fuel injection nozzles that are provided in a leading end part of the nozzle body at predetermined intervals in a circumferential direction and extend through the cover ring so as to be able to inject fuel from the fuel flow passage toward the front side. The cover ring has an outer circumferential surface cover that covers an outer circumferential surface of the nozzle body, a leading end surface cover that covers a leading end surface of the nozzle body, and a plurality of inclined flow passages that extend through the leading end surface cover in a thickness direction and are inclined in a predetermined direction relative to a direction of a central axis.

First claim

The invention claimed is:

1. A combustor nozzle, comprising:
a nozzle body that is provided with a fuel flow passage and extends in a rod shape;
a cover ring that is disposed on an outer side of an outer circumference of a leading end of the nozzle body with a predetermined clearance thereto so as to form an air flow passage that allows air to jet out toward a front side; and
fuel injection nozzles that are provided in a leading end part of the nozzle body at predetermined intervals in a circumferential direction and extend through the cover ring so as to be able to inject fuel from the fuel flow passage toward the front side,
wherein the cover ring has:
an outer circumferential surface cover that has a cylindrical shape and covers an outer circumferential surface of the nozzle body;
a leading end surface cover that has an annular shape and covers a leading end surface of the nozzle body; and
inclined flow passages that extend through the leading end surface cover in a thickness direction and are inclined in a predetermined direction relative to a central axis direction of the nozzle body.

2. The combustor nozzle according to claim 1 , wherein the inclined flow passages are inclined along a circumferential direction of the cover ring.

3. The combustor nozzle according to claim 2 , further comprising a swirling force application part that applies a swirling force to an air current flowing through the air flow passage, wherein the inclined flow passages are inclined along a direction in which air is swirled by the swirling force application part.

4. The combustor nozzle according to claim 3 , wherein the inclined flow passages are composed of a plurality of inclined flow passages having different inclination angles.

5. The combustor nozzle according to claim 4 , wherein the inclination angles of the plurality of inclined flow passages are set so as to become larger toward a downstream side in the direction in which air is swirled by the swirling force application part.

6. The combustor nozzle according to claim 1 , wherein the inclined flow passages are inclined relative to a direction perpendicular to a surface of the cover ring.

7. The combustor nozzle according to claim 1 , wherein the inclined flow passages are through-holes that extend through the cover ring in a plate thickness direction.

8. The combustor nozzle according to claim 1 , wherein the inclined flow passages are slits that extend through the cover ring in the plate thickness direction and extend along a radial direction of the cover ring.

9. The combustor nozzle according to claim 8 , wherein one end in a longitudinal direction of each of the slits is open in an inner circumference of the leading end surface cover.

10. The combustor nozzle according to claim 1 , wherein
the leading end surface cover is provided with a first front surface that is orthogonal to the central axis direction and a second front surface that is inclined relative to a direction orthogonal to the central axis direction, and
the inclined flow passages are open in the first front surface and the second front surface.

11. The combustor nozzle according to claim 10 , wherein an inclination direction of the inclined flow passages provided in the first front surface and an inclination direction of the inclined flow passages provided in the second front surface are different from each other.

12. The combustor nozzle according to claim 1 , wherein the inclined flow passages extend along the radial direction of the cover ring and are inclined so as to face the central axis direction.

13. The combustor nozzle according to claim 1 , wherein the cover ring has a plurality of grooves that are provided in a rear surface of the leading end surface cover and extend along the radial direction of the leading end surface cover.

14. A gas turbine combustor, comprising:
a cylinder in which high-pressure air and fuel are combusted to generate combustion gas;
a pilot combustion burner that is disposed at a central part inside the cylinder; and
a plurality of main combustion burners that are disposed so as to surround the pilot combustion burner inside the cylinder,
wherein the pilot combustion burner has the combustor nozzle according to claim 1 .

15. A gas turbine, comprising:
a compressor that compresses air;
the gas turbine combustor according to claim 14 that mixes together compressed air compressed by the compressor and fuel and combusts the mixture; and
a turbine that produces rotary power from combustion gas generated by the gas turbine combustor.

16. A cover ring, comprising:
an outer circumferential surface cover that has a cylindrical shape with a central axis;
a leading end surface cover that has an annular shape inclined from a leading end part of the outer circumferential surface cover toward a central axis side and a leading end side;
a through-hole that extends through the leading end surface cover in a thickness direction;
inclined flow passages that extend through the leading end surface cover in the thickness direction and are inclined in a predetermined direction relative to the central axis,
wherein the cover ring is configured to be disposed on an outer side of an outer circumference of a leading end of a nozzle body with a predetermined clearance thereto so as to form an air flow passage that allows air to jet out toward a front side.

17. The cover ring according to claim 16 , wherein
a plurality of through-holes are provided at predetermined intervals in a circumferential direction of the leading end surface cover, and
more than one of the inclined flow passages are provided between the plurality of through-holes.

18. The cover ring according to claim 16 , wherein the inclined flow passages are inclined along the circumferential direction of the leading end surface cover.

19. The cover ring according to claim 16 , wherein the inclined flow passages are composed of a plurality of inclined flow passages having different inclination angles.

20. The cover ring according to claim 16 , wherein the through-hole has an inlet that is open in a rear surface of the leading end surface cover and an outlet that is open in a front surface of the leading end surface cover, the through-hole providing communication between the inlet and the outlet,
and wherein each inclined flow passage has an inlet that is open in the rear surface of the leading end surface cover and an outlet that is open in the front surface of the leading end surface cover and provides communication between the inlet and the outlet.

21. A combustor nozzle manufacturing method comprising mounting a cover ring on an outer side of an outer circumference of a leading end of a nozzle body with a predetermined clearance thereto, the cover ring having an outer circumferential surface cover that has a cylindrical shape and covers an outer circumferential surface of the nozzle body, a leading end surface cover that has an annular shape and covers a leading end surface of the nozzle body, a through-hole that extends through the leading end surface cover in a thickness direction, and inclined flow passages that extend through the leading end surface cover in the thickness direction and are inclined in a predetermined direction relative to a central axis direction of the nozzle body,
wherein the through-hole has an inlet that is open in a rear surface of the leading end surface cover and an outlet that is open in a front surface of the leading end surface cover, the through-hole providing

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Mitani Masaki
• Fukumoto Koshiro
• Saito Toshihiko
• Isono Mitsunori
• Morishige Dai
• Izutsu Nobuyuki
• Yamasaki Hiroyuki
• Wada Yoshiyuki

Classifications

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/286 Primary

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

• F23R3/283 Primary

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title