VENTILATION SYSTEM FOR TURBOMACHINE USING BLADELESS AIRFLOW AMPLIFIER

• US 20170306845A1
• Filed: 04/22/2016
• Published: 10/26/2017
• Est. Priority Date: 04/22/2016
• Status: Active Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Laing, Donald Gordon, Cordova Magaa, Jose Antonio, Gonzalez Tellez, Victor Alfonso, Sanchez Rubio, Oswaldo Alberto
• Application Number:
  US15/135,866
• Publication Number:
  US 20170306845A1
• Time in Patent Office: Days
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A ventilation system for a turbomachine enclosure includes: a bladeless airflow amplifier configured to pass an airflow through at least a portion of the turbomachine enclosure; and an amplifier airflow source fluidly coupled to the bladeless airflow amplifier for providing an operative airflow to operate the bladeless airflow amplifier. The ventilation system may be employed with or without a conventional vent fan system.

Claims

1. A ventilation system for a turbomachine enclosure, the ventilation system comprising:

a bladeless airflow amplifier configured to pass an airflow through at least a portion of the turbomachine enclosure; and

an amplifier airflow source fluidly coupled to the bladeless airflow amplifier for providing an operative airflow to operate the bladeless airflow amplifier.

2. The ventilation system of claim 1, wherein the bladeless airflow amplifier is coupled to an airflow outlet opening in the turbomachine enclosure to pass the airflow out of the turbomachine enclosure.

3. The ventilation system of claim 2, further comprising another bladeless airflow amplifier fluidly coupled to the amplifier airflow source, the another bladeless airflow amplifier coupled to another airflow outlet opening in a portion of the turbomachine enclosure.

4. The ventilation system of claim 1, wherein the bladeless airflow amplifier is coupled to an airflow inlet opening in the turbomachine enclosure to pass the airflow into the turbomachine enclosure.

5. The ventilation system of claim 1, wherein the bladeless airflow amplifier includes a first bladeless airflow amplifier coupled to an airflow outlet opening in the turbomachine enclosure to pass the airflow out of the turbomachine enclosure, and a second bladeless airflow amplifier coupled to an airflow inlet opening in the turbomachine enclosure to pass the airflow through the turbomachine enclosure.

6. The ventilation system of claim 5, wherein the amplifier airflow source includes a first amplifier airflow source fluidly coupled to the first bladeless airflow amplifier for providing a first operative airflow to operate the first bladeless airflow amplifier, and a second amplifier airflow source fluidly coupled to the second bladeless airflow amplifier for providing a second operative airflow to operate the second bladeless airflow amplifier.

7. The ventilation system of claim 1, wherein the turbomachine includes a gas turbine engine and an exhaust collector operatively coupled to the gas turbine engine, and

wherein the bladeless airflow amplifier includes a first bladeless airflow amplifier coupled to a first airflow outlet opening upstream of the exhaust collector and a second bladeless airflow amplifier coupled to a second airflow outlet opening downstream of the exhaust collector.

8. The ventilation system of claim 1, wherein the amplifier airflow source includes a plurality of amplifier airflow sources fluidly coupled to the bladeless airflow amplifier to provide the operative airflow.

9. The ventilation system of claim 1, wherein the amplifier airflow source includes a cooling fan of a generator that is operatively coupled to a turbomachine, the cooling fan providing at least a portion of the operative airflow.

10. The ventilation system of claim 1, wherein the amplifier airflow source includes a compressor configured to provide an airflow to a turbomachine, the compressor providing at least a portion of the operative airflow, and

further comprising a regulating valve to modulate the airflow from the compressor for use as the amplifier airflow source.

11. The ventilation system of claim 1, wherein the bladeless airflow amplifier includes a plurality of bladeless airflow amplifiers, each bladeless airflow amplifier coupled to a separate turbomachine enclosure, and

wherein the amplifier airflow source fluidly couples to each of the plurality of bladeless airflow amplifiers for providing the operative airflow to operate each of the plurality of bladeless airflow amplifiers.

12. The ventilation system of claim 1, further comprising an internal bladeless airflow amplifier positioned within the turbomachine enclosure.

13. The ventilation system of claim 12, wherein the internal bladeless airflow amplifier surrounds at least a portion of a turbomachine.

14. A system, comprising:

a gas turbine engine enclosure;

a gas turbine engine disposed in the gas turbine engine enclosure; and

a ventilation system coupled to the gas turbine engine enclosure, wherein the ventilation system includes;

a bladeless airflow amplifier configured to pass an airflow through at least a portion of the gas turbine engine enclosure, and

an amplifier airflow source fluidly coupled to the bladeless airflow amplifier for providing an operative airflow to operate the bladeless airflow amplifier.

15. The system of claim 14, wherein the bladeless airflow amplifier is coupled to an airflow outlet opening in the gas turbine engine enclosure to pass the airflow out of the gas turbine engine enclosure.

16. The system of claim 15, further comprising another bladeless airflow amplifier fluidly coupled to the amplifier airflow source, the another bladeless airflow amplifier coupled to another airflow outlet opening in a portion of the gas turbine engine enclosure.

17. The system of claim 14, wherein the bladeless airflow amplifier is coupled to an airflow inlet opening in the gas turbine engine enclosure to pass the airflow into the gas turbine engine enclosure.

18. The system of claim 14, wherein the bladeless airflow amplifier includes a first bladeless airflow amplifier coupled to an airflow outlet opening in the gas turbine engine enclosure to pass the airflow out of the gas turbine engine enclosure, and a second bladeless airflow amplifier coupled to an airflow inlet opening in the gas turbine engine enclosure to pass the airflow through the gas turbine engine enclosure.

19. The system of claim 18, wherein the amplifier airflow source includes a first amplifier airflow source fluidly coupled to the first bladeless airflow amplifier for providing a first operative airflow to operate the first bladeless airflow amplifier, and a second amplifier airflow source fluidly coupled to the second bladeless airflow amplifier for providing a second operative airflow to operate the second bladeless airflow amplifier.

20. The system of claim 14, further comprising an exhaust collector operatively coupled to the gas turbine engine, and

wherein the bladeless airflow amplifier includes a first bladeless airflow amplifier coupled to a first airflow outlet opening upstream of the exhaust collector and a second bladeless airflow amplifier coupled to a second airflow outlet opening downstream of the exhaust collector.