Compensating for thermal expansion via controlled tube buckling

Patent metadata

Field	Value
Publication number	US-9625155-B2
Application number	US-201414147240-A
Country	US
Kind code	B2
Filing date	Jan 3, 2014
Priority date	Jan 3, 2014
Publication date	Apr 18, 2017
Grant date	Apr 18, 2017

Abstract

One embodiment includes a fuel injector for a gas turbine engine. The fuel injector has an inlet fitting for receiving fuel. The fuel injector also has an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine. An injector support extends between the inlet fitting and the outlet fitting and has an internal bore therethrough. A fuel tube extends from the inlet fitting through the internal bore of the injector support to the outlet fitting. The injector support has a greater coefficient of thermal expansion than the fuel tube. At room temperature the fuel tube is under compressive stress such that the fuel tube is buckled. As a result of differential thermal expansion of the fuel tube and the injector support during engine operation the fuel tube is relieved of compressive stress.

First claim

The invention claimed is:

1. A fuel injector for a gas turbine engine, the fuel injector comprising:
an inlet fitting for receiving fuel;
an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine;
an injector support extending between the inlet fitting and the outlet fitting having an internal bore therethrough; and
a fuel tube extending from the inlet fitting through the internal bore of the injector support to the outlet fitting; wherein the injector support has a greater coefficient of thermal expansion than the fuel tube, and wherein at room temperature the fuel tube is under compressive stress such that the fuel tube is buckled, and wherein as a result of differential thermal expansion of the fuel tube and the injector support during engine operation the fuel tube is relieved of compressive stress.

2. The fuel injector of claim 1 , wherein the fuel tube is initially imparted with compressive stress and buckles during a braze cycle.

3. The fuel injector of claim 1 , wherein the fuel tube has a slenderness ratio of 90 or greater.

4. The fuel injector of claim 1 , wherein the injector support is made of stainless steel having a chemical composition by weight including approximately 16-26% chromium and 8-22% nickel, a maximum of 0.25% carbon, a maximum of 2% manganese, a maximum of 0.045% phosphorus, a maximum of 0.03% sulfur, a maximum of 1.5% silicon, and a maximum of 4% molybdenum.

5. The fuel injector of claim 4 , wherein the fuel tube is made of a material having a chemical composition by weight including 3.15-4.15% niobium plus tantalum, 8-10% molybdenum, 20-23% chromium, a maximum of 5% iron, and a minimum of 58% nickel.

6. The fuel injector of claim 4 , wherein the fuel tube is made of a material having a chemical composition by weight including approximately 22% chromium, 18% iron, 9% molybdenum, 1.5% cobalt, 0.6% tungsten, and 0.1% carbon, a maximum of 1% manganese, a maximum of 1% silicone, a maximum of 0.008% boron, and a remaining balance of approximately 47% nickel.

7. The fuel injector of claim 4 , wherein the fuel tube is made of stainless steel having a chemical composition by weight including approximately 11.5-18% chromium, a maximum of 1.2% carbon, a maximum of 1.25% manganese, a maximum of 0.06% phosphorus, a maximum of 0.03% sulfur, a maximum of 0.06% nitrogen, a maximum of 1% silicone, a maximum of 0.55% nickel, and a maximum of 0.75% molybdenum.

8. The fuel injector of claim 1 , further comprising multiple fuel tubes extending from the inlet fitting through the internal bore of the injector support to the outlet fitting.

9. The fuel injector of claim 1 , wherein a first end of the fuel tube is fixed to the inlet fitting.

10. A fuel injector for a gas turbine engine, the fuel injector comprising:
an inlet fitting for receiving fuel;
an outlet fitting for delivering fuel through a nozzle to a combustor of the gas turbine engine;
an injector support extending between the inlet fitting and the outlet fitting having an internal bore therethrough; and
a first fuel tube positioned in the inlet fitting and extending through the internal bore of the injector support to the outlet fitting, wherein the injector support has a greater coefficient of thermal expansion than the first fuel tube, and wherein the first fuel tube is fixed to the outlet fitting.

11. The fuel injector of claim 10 , wherein the first fuel tube has a slenderness ratio of 90 or greater.

12. The fuel injector of claim 10 , further comprising a second fuel tube extending parallel to the first fuel tube and positioned adjacent to the first fuel tube, wherein the injector support has a greater coefficient of thermal expansion than the second fuel tube, and wherein the second fuel tube is fixed to the outlet fitting.

13. The fuel injector of claim 10 , wherein each of the first and second fuel tubes has a slenderness ratio of 90 or greater.

14. The fuel injector of claim 10 , wherein the first fuel tube has a thermal expansion coefficient of approximately 16.38×10 −6 cm/cm ° C. (9.1×10 −6 in./in.° F.) and the injector support has a coefficient of thermal expansion of approximately 19.98×10 −6 cm/cm ° C. (11.1×10 −6 in./in.° F.).

Assignees

• Delavan Inc

Inventors

• Caples Mark

Classifications

• Y10T29/49945

  by driven force fit · CPC title

• F23R3/283 Primary

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

• Y10T29/49865

  by temperature differential [e.g., shrink fit] · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title