# US 10,760,495 B2 · Fluid manifold for gas turbine engine and method for delivering fuel to a combustor using same

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 10,760,495 B2
- Document ID: US10760495B2
- Status: Granted
- Kind: B2
- Application number: 15/975,895
- Filed: 2018-05-10
- Published: 2018-09-13
- Granted: 2020-09-01
- Earliest claimed: 2013-12-20
- Assignees: Pratt & Whitney Canada Corp.
- Applicants: Pratt & Whitney Canada Corp.
- Inventors: Eduardo David Hawie; Nigel Caldwell Davenport; Jian-Ming Zhou
- Web page: https://patentgrep.com/patent/US10760495B2

## CPC

- F02C 7/222: {Fuel flow conduits, e.g. manifolds}
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)

## Abstract

A method for delivering fuel to a combustor of a gas turbine engine includes: injecting fuel into a conduit of a fuel manifold; directing the fuel through a continuous first portion of the conduit; directing the fluid from the first portion into an inflexion of the conduit being a single exit of the first portion; directing the fuel from the inflexion into a second portion of the conduit in serial flow communication with the first portion; and carrying the fuel in the second portion in a direction different from that of the fuel in the first portion. As the fuel flows through the second portion of the conduit, the fuel exits from the second portion of the conduit into a plurality of fuel injection nozzles in exclusive fluid flow communication with the second portion for ejection into a combustor of the gas turbine engine.

## Claims

### Claim 1

A method for delivering fuel to a combustor of a gas turbine engine, the method comprising:
injecting fuel into a conduit of a fuel manifold via a conduit inlet, the fuel manifold having a ring-shaped body;
directing the fuel through a continuous first portion of the conduit extending between the conduit inlet and an inflexion of the conduit, the first portion of the conduit disposed in a first half of the ring-shaped body;
directing the fluid through the inflexion of the conduit, the inflexion forming a single exit of the first portion and being U-shaped, the inflexion located opposite from the conduit inlet relative to the ring-shaped body;
directing the fuel through a second portion of the conduit in serial flow communication with the first portion, the second portion of the conduit extending downstream from the inflexion, wherein fuel flowing in the second portion flows in a direction opposite to that of the fuel flowing in the first portion, the second portion of the conduit disposed in said first half of the ring-shaped body; and
as the fuel flows through the second portion of the conduit, exiting the fuel from the second portion of the conduit into a first group of fuel injection nozzles in exclusive fluid flow communication with the second portion for ejection into the combustor of the gas turbine engine.

### Claim 2 (depends on 1)

The method as defined in claim 1, further comprising at least partially cooling the fuel manifold as a result of directing the fuel through the first portion of the conduit.

### Claim 3 (depends on 1)

The method as defined in claim 1, further comprising flowing the fuel at a constant velocity as the fuel flows through the second portion of the conduit.

### Claim 4 (depends on 1)

The method as defined in claim 1, further comprising:
injecting fuel into a second conduit of the fuel manifold via the conduit inlet;
directing the fuel through a continuous first portion of the second conduit extending between the conduit inlet and an inflexion of the second conduit, the first portion of the second conduit disposed in a second half of the ring-shaped body of the fuel manifold;
directing the fluid through the inflexion of the second conduit, the inflexion of the second conduit forming a single exit of the first portion of the second conduit and being U-shaped, the inflexion of the second conduit located opposite from the conduit inlet relative to the ring-shaped body;
directing the fuel through a second portion of the second conduit in serial flow communication with the first portion of the second conduit, the second portion of the second conduit extending downstream from the inflexion of the second conduit, wherein fuel flowing in the second portion of the second conduit flows in a direction opposite to that of the fuel flowing in the first portion of the second conduit, the second portion of the second conduit disposed in said second half of the ring-shaped body; and
as the fuel flows through the second portion of the second conduit, exiting the fuel from the second portion of the second conduit into a second group of fuel injection nozzles in exclusive fluid flow communication with the second portion of the second conduit for ejection into the combustor of the gas turbine engine.