Tangential on-board injectors for gas turbine engines

Patent metadata

Field	Value
Publication number	US-2017082027-A1
Application number	US-201514860167-A
Country	US
Kind code	A1
Filing date	Sep 21, 2015
Priority date	Sep 21, 2015
Publication date	Mar 23, 2017
Grant date	—

Abstract

A tangential on-board injector (TOBI) for a gas turbine engine is provided. The TOBI includes a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit and a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity. The purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.

First claim

What is claimed is:

1 . A tangential on-board injector (TOBI) for a gas turbine engine, the TOBI comprising:
a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit; and a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity, wherein the purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.

2 . The tangential on-board injector of claim 1 , wherein the purge cavity is configured to expel particles from the purge cavity to an annular cavity external to the body.

3 . The tangential on-board injector of claim 1 , further comprising an inlet extension connected to the entrance of the body, the inlet extension extending from the body and having an inlet configured to force air to change direction when entering the inlet of the inlet extension.

4 . The tangential on-board injector of claim 3 , wherein the inlet extension is configured to direct air through an angle as the air flows through the inlet extension.

5 . The tangential on-board injector of claim 4 , wherein the angle is equal to or greater than 90°.

6 . The tangential on-board injector of claim 1 , wherein the purge cavity is integrally formed with the body.

7 . The tangential on-board injector of claim 1 , further comprising a separator located at the exit of the body, the separator configured to separate an airflow flowing through the air passageway into a first flow path and a second flow path.

8 . The tangential on-board injector of claim 7 , wherein the first flow path is directed inboard relative to the body and the first flow path is directed outboard relative to the body.

9 . The tangential on-board injector of claim 7 , wherein each of the first flow path and the second flow path are configured to direct air to cool components of a gas turbine engine.

10 . A method of manufacturing a gas turbine engine having a tangential on-board injector, the method comprising:
forming a purge cavity on an exterior surface of a body of the tangential on-board injector, the purge cavity having a purge cavity entry fluidly connecting an air passageway of the body to the purge cavity.

11 . The method of claim 10 , wherein the purge cavity is configured to expel particles from the purge cavity to an annular cavity external to the body.

12 . The method of claim 10 , wherein the purge cavity is integrally formed with the body of the tangential on-board injector.

13 . The method of claim 10 , further comprising installing an inlet extension to the entrance of the body, the inlet extension extending from the body and having an inlet configured to force air to change direction when entering the inlet of the inlet extension.

14 . The method of claim 13 , wherein the inlet extension is configured to direct air through an angle as the air flows through the inlet extension.

15 . The method of claim 14 , wherein the angle is equal to or greater than 90°.

16 . The method of claim 10 , further comprising forming a separator at an exit of the body, the separator configured to separate an airflow flowing through the body into a first flow path and a second flow path.

17 . A gas turbine engine comprising:
tangential on-board injector having:
a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit; and
a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity,
wherein the purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.

18 . The gas turbine engine of claim 17 , wherein the purge cavity is configured to expel particles from the purge cavity to an annular cavity external to the body.

19 . The gas turbine engine of claim 17 , further comprising an inlet extension connected to the entrance of the body, the inlet extension extending from the body and having an inlet configured to force air to change direction when entering the inlet of the inlet extension.

20 . The gas turbine engine of claim 17 , further comprising a separator located at the exit of the body, the separator configured to separate an airflow flowing through the air passageway into a first flow path and a second flow path.

Assignees

• United Technologies Corp

Inventors

• Zelesky Mark F
• Wagner Joel H
• Ahmadian Shayan

Classifications

• F05D2260/14

  Preswirling · CPC title

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F05D2260/607

  Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title