Cooled cooling air taken directly from combustor dome

Patent metadata

Field	Value
Publication number	US-10151243-B2
Application number	US-201615060734-A
Country	US
Kind code	B2
Filing date	Mar 4, 2016
Priority date	Feb 23, 2013
Publication date	Dec 11, 2018
Grant date	Dec 11, 2018

Abstract

A gas turbine engine includes a compressor, a turbine, and a combustor. The combustor includes a fuel injector and a vaporizer within the combustor positioned to receive liquid fuel from the fuel injector to vaporize the liquid fuel therein. The gas turbine engine includes an enclosed passage external to the combustor having a wall, a diffuser positioned to direct the air into the passage, causing the air to cool by transferring heat through the wall from the air within the passage to the vaporized fuel within the vaporizer, and a cooled cooling air passageway positioned to receive the air from the passage and direct the air after being cooled to at least one of the turbine and the compressor.

First claim

The invention claimed is:

1. A combustor assembly for a gas turbine engine, the combustor assembly comprising:
an outer casing;
an inner casing;
at least one liner defining an inner combustion volume;
an exterior volume defined between the outer casing and the inner casing, a first portion of the exterior volume being defined between the outer casing and the inner combustion volume, a second portion of the exterior volume being defined between the inner casing and the inner combustion volume, and a third portion of the exterior volume extending forward of the inner combustion volume;
a fuel injector;
a vaporizer within the inner combustion volume and positioned to receive liquid fuel from the fuel injector, the vaporizer being configured to vaporize the liquid fuel to form a vaporized fuel;
an enclosed passage external to the inner combustion volume and positioned at a forward end of the inner combustion volume, the enclosed passage having an inlet positioned between the outer casing and the inner casing in the third portion of the exterior volume, a first wall portion in common with the inner combustion volume, a second wall portion extending from the inlet and connected to the inner casing, and a third wall portion, wherein the first wall portion is a portion of the at least one liner, the enclosed passage configured to receive air from a diffuser, wherein the received air is cooled in the enclosed passage via heat transfer through the first wall portion from the received air within the enclosed passage to the vaporized fuel within the vaporizer; and
a cooled cooling air passageway positioned to receive the cooled air from the enclosed passage and split a flow of the cooled air to direct a first portion of the flow of the cooled air to a turbine and a second portion of the flow of the cooled air to a compressor;
wherein the third wall portion of the enclosed passage extends from the first wall portion and across the second portion of the exterior volume and is connected to the cooled cooling air passageway.

2. The combustor assembly as claimed in claim 1 , wherein the vaporized fuel flows within the vaporizer in parallel with, and in the same direction as, the air flowing within the enclosed passage.

3. The combustor assembly as claimed in claim 1 , wherein the vaporized fuel is directed toward the first wall portion.

4. The combustor assembly as claimed in claim 1 , wherein the first portion of the flow of the cooled air passes through a portion of the cooled cooling air passageway, the portion of the cooled cooling air passageway extending aft of a flow split location at which the flow of the cooled air is split into the first portion of the flow of the cooled air and the second portion of the flow of the cooled air.

5. A gas turbine engine, comprising:
a compressor having a diffuser;
a turbine; and
a combustor assembly, comprising:
an outer casing;
an inner casing;
at least one liner defining an inner combustion volume;
an exterior volume defined between the outer casing and the inner casing, a first portion of the exterior volume being defined between the outer casing and the inner combustion volume, a second portion of the exterior volume being defined between the inner casing and the inner combustion volume, and a third portion of the exterior volume extending forward of the inner combustion volume;
a fuel injector;
a vaporizer within the inner combustion volume, the vaporizer being positioned to receive liquid fuel from the fuel injector to vaporize the liquid fuel therein;
an enclosed passage external to the inner combustion volume and positioned at a forward end of the inner combustion volume, the enclosed passage having an inlet positioned between the outer casing and the inner casing in the third portion of the exterior volume, a first wall portion in common with the inner combustion volume, a second wall portion extending from the inlet and connected to the inner casing, and a third wall portion, wherein the first wall portion is a portion of the at least one liner,
the enclosed passage being configured to receive air from the diffuser, wherein the air within the enclosed passage is cooled via heat transfer through the first wall portion from the air within the enclosed passage to the vaporized fuel within the vaporizer; and
a cooled cooling air passageway positioned to receive the air from the enclosed passage, split a flow of the air at a flow split location, and direct a first portion of the flow of the air to the turbine and a second portion of the flow of the air to the compressor;
wherein the third wall portion of the enclosed passage extends from the first wall portion and across the second portion of the exterior volume and is connected to the cooled cooling air passageway.

6. The gas turbine engine as claimed in claim 5 , wherein the vaporized fuel flows within the vaporizer in parallel with, and in the same direction as, the air flowing within the enclosed passage.

7. The gas turbine engine as claimed in claim 5 , wherein the vaporized fuel is directed toward the first wall portion.

8. The gas turbine engine as claimed in claim 5 , wherein the first portion of the flow of the air passes through a portion of the cooled cooling air passageway, the portion of the cooled cooling air passageway extending aft of the flow split location.

Assignees

• Rolls Royce Corp

Inventors

• Smith Duane A
• Cummings Iii William G

Classifications

• F23R3/32

  being tubular · CPC title

• Y02T50/676

  Cross-Sectional Technologies · mapped topic

• F05D2260/207

  using a phase changing mass, e.g. heat absorbing by melting or boiling · CPC title

• F02C3/24

  the fuel or oxidant being liquid at standard temperature and pressure · CPC title

• F02C7/185 Primary

  Cooling means for reducing the temperature of the cooling air or gas · CPC title