Integral rotor bore and bore basket

Patent metadata

Field	Value
Publication number	US-11067090-B1
Application number	US-202016797839-A
Country	US
Kind code	B1
Filing date	Feb 21, 2020
Priority date	Feb 21, 2020
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

An apparatus is provided that includes a rotor bore and a bore basket. The bore basket extends axially between a first and second axial ends. The bore basket includes an engagement panel, and cylindrical inner and outer radial panels. The inner and outer radial panels extend substantially between the first and second axial ends. The inner radial panel is disposed radially inside of and separated from the outer radial panel, defining an annular passage disposed there between. The bore basket includes a plurality of inlet apertures in fluid communication with the annular passage at a first axial position, and a plurality of exit apertures in fluid communication with the annular passage at a second axial position. The second axial end of the bore basket is attached to an inner radial hub of the rotor bore, and the rotor bore and bore basket are a unitary structure.

First claim

What is claimed is:

1. An apparatus, comprising:
a rotor bore having an inner radial hub;
a bore basket extending axially between a first axial end and a second axial end opposite the first axial end, the bore basket having:
an engagement panel disposed at the first axial end;
a cylindrical inner radial panel;
a cylindrical outer radial panel, wherein the inner radial panel and the outer radial panel extend substantially between the first axial end and the second axial end, and the inner radial panel is disposed radially inside of and separated from the outer radial panel, and an annular passage is disposed between the inner radial panel and the outer radial panel;
a plurality of inlet apertures in fluid communication with the annular passage at a first axial position; and
a plurality of exit apertures in fluid communication with the annular passage at a second axial position, the second axial position separated from the first axial position;

wherein the second axial end of the bore basket is attached to the inner radial hub of the rotor bore, and the rotor bore and bore basket are a unitary structure.

2. The apparatus of claim 1 , wherein the plurality of inlet apertures extend through the outer radial panel at the first axial position.

3. The apparatus of claim 1 , wherein the plurality of exit apertures extend through the outer radial panel at the second axial position.

4. The apparatus of claim 1 , wherein the plurality of inlet apertures and the plurality of exit apertures are circumferentially disposed around the outer radial panel.

5. The apparatus of claim 1 , wherein the rotor bore and the bore basket comprise the same material.

6. The apparatus of claim 1 , wherein the inner radial panel and the outer radial panel are welded to one another, and the bore basket and the rotor bore are welded to one another.

7. A gas turbine engine rotor section, comprising:
a plurality of rotor stages, each rotor stage having a rotor bore with an inner radial hub, the rotor stages connected to one another by a hub structure, the hub structure in part defining a bore cavity; and
a bore basket extending axially between a first axial end and a second axial end opposite the first axial end, the bore basket having:
an engagement panel disposed at the first axial end;
a cylindrical inner radial panel;
a cylindrical outer radial panel, wherein the inner radial panel and the outer radial panel extend substantially between the first axial end and the second axial end, and the inner radial panel is disposed radially inside of and separated from the outer radial panel, and an annular passage is disposed between the inner radial panel and the outer radial panel;
a plurality of inlet apertures in fluid communication with the annular passage at a first axial position; and
a plurality of exit apertures in fluid communication with the annular passage at a second axial position, the second axial position axially separated from the first axial position;

wherein the bore basket is integrally formed with a first rotor bore of a first rotor stage of the plurality of rotor stages, and the second axial end of the bore basket extends outwardly from the inner radial hub of the first rotor bore; and
wherein the engagement panel is connected to the hub structure; and
wherein the hub structure, the bore basket, and the first rotor bore define a sub-section of the bore cavity, the sub-section including a second rotor bore of a second rotor stage of the plurality of rotor stages.

8. The rotor section of claim 7 , wherein the plurality of inlet apertures extend through the outer radial panel at the first axial position.

9. The rotor section of claim 8 wherein the plurality of exit apertures extend through the outer radial panel at the second axial position.

10. The rotor section of claim 9 , wherein the plurality of inlet apertures and the plurality of exit apertures are circumferentially disposed around the outer radial panel.

11. The rotor section of claim 7 , wherein the first rotor bore and the bore basket comprise the same material.

12. The rotor section of claim 7 , wherein the inner radial panel and the outer radial panel are welded to one another, and the bore basket and the first rotor bore are welded to one another.

13. The rotor section of claim 7 , wherein the hub structure (HS) includes a plurality of HS inlet apertures and a plurality of HS exit apertures, and the plurality of HS inlet apertures and the plurality of HS exit apertures in fluid communication with the sub-section of the bore cavity.

14. The rotor section of claim 7 , wherein the sub-section is located at a forward portion of the bore cavity.

15. The rotor section of claim 7 , wherein the sub-section is located at an aft portion of the bore cavity.

16. The rotor section of claim 7 , further comprising a second bore basket having:
a second engagement panel;
a second cylindrical inner radial panel;
a second cylindrical outer radial panel, wherein the second inner radial panel and the second outer radial panel extend axially, and the second inner radial panel is disposed radially inside of and separated from the second outer radial panel, and a second annular passage is disposed between the second inner radial panel and the second outer radial panel;
a plurality of second inlet apertures in fluid communication with the second annular passage; and
a plurality of second exit apertures in fluid communication with the second annular passage, the second inlet apertures axially separated from the second exit apertures;
wherein the second bore basket is integrally formed with a third rotor bore of a third rotor stage of the plurality of rotor stages, and extends outwardly from the inner radial hub of the third rotor bore; and
wherein the second engagement panel is connected to the hub structure; and
wherein the hub structure, the second bore basket, and the third rotor bore define a second sub-section of the bore cavity, the second sub-section including a fourth rotor bore of a fourth rotor stage of the plurality of rotor stages.

17. The rotor section of claim 7 , wherein the rotor section is a compressor section.

18. The rotor section of claim 7 , wherein the rotor section is a turbine section.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Giannakopoulos Konstantinos P

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/084 Primary

  the fluid circulating at the periphery of a multistage rotor, e.g. of drum type · CPC title

• F04D29/053

  Shafts · CPC title

• F05D2220/3216

  for a special compressor stage · CPC title

• F05D2240/61

  Hollow · CPC title