Method and apparatus for producing fluid pressure and controlling boundary layer

• US 5,152,661 A
• Filed: 04/20/1990
• Issued: 10/06/1992
• Est. Priority Date: 05/27/1988
• Status: Expired due to Fees

• Current Assignee: Herman E. Sheets
• Original Assignee: Herman E. Sheets
• Inventors: Sheets, Herman E.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, HOANG M
• Application Number:
  US07/513,495
• Time in Patent Office: 900 Days
• Field of Search: 415/203, 415/206, 415/208.1, 415/209.1, 415/181, 415/208.4, 415/211.2, 415/83, 415/84, 415/149.2
• US Class Current: 415/84
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/146 of blades with tandem configuration, split blades or slotted blades
• CPC Class Codes: F04D 17/127 with radially spaced stages, e.g. for contrarotating type
• CPC Class Codes: F04D 29/18 Rotors specially for elastic fluids F04D29/26
• CPC Class Codes: F04D 29/30 Vanes
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: F04D 29/44 Fluid-guiding means, e.g. diffusers
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F04D 29/682 by fluid extraction

Abstract

This invention relates to a blower of a centrifugal turbomachine type for producing fluid pressure from mechanical energy. The invention relates to the guide vane rows or vaned diffuser used in centrifugal blowers. The vaned diffuser is located downstream by the impeller. The impellers of the centrifugal blowers can have blades which are backwardly curved, radially ending or forwardly curved. Each of these impellers can have a vaned or vaneless diffusing system following the impeller. During operation of the impeller blades at the design point, the average outlet relative velocity is equal to or greater than 0.6 times the inlet relative velocity at the hub of the impeller portion of the impeller blades and the angle of flow deflection within the impeller blades is at least equal to approximately 50° or more. The centrifugal turbomachine also includes a series of guide vane rows, each of said guide vane rows, including at least a forward row of blades and an aft row of blades. The chord of each of the blades in the aft row is greater than the chord of each of the blades in the forward row and each blade in the aft row cooperates with the corresponding blade in the forward row to form, during operation of the centrifugal turbomachine, multiple rows of blades. The pressure coefficient for each centrifugal blower stage is greater than approximately 1.1.

Claims

1. In the blower of the centrifugal turbomachine type,

a. a stationary annular member.

b. an impeller positioned for rotation in said stationary annular member and being radially spaced therefrom by an annular fluid path which has a fluid inlet end and a fluid outlet end of larger diameter and which has a curved flow channel of progressively increasing area which extends from said fluid inlet end to said fluid outlet end,

c. a series of impeller blade rows located in said fluid flow path and being connected to said impeller and a series of guide vane rows located in said flow path and being connected to said annular stationary member, said guide vane rows being alternated with said impeller blade rows along said flow path, each of said impeller blade rows in conjunction with an adjacent one of said guide vane rows constituting one of a series of pressure generation stages in said curved portion of said flow path,

(1) each of said impeller blades having an impeller portion, an outer blade portion, a rounded leading edge and a relatively sharp trailing edge, and a combination of camber and solidity wherein, during operation of said impeller blades at the design point,

(a) the average outlet relative velocity is equal to or greater than 0.6 times the inlet relative velocity at the hub of the impeller portion of said blades, and

(b) the angle of flow deflection within the impeller blades is at least equal to approximately 50°

or more,

(2) each of said guide vane rows including at least a forward row of blades and an aft row of blades,

(a) the chord of each of the blades in the aft row being greater than the chord of each of the blades in the forward row,

(b) each blade in the aft row cooperating with the corresponding blade in the forward row to form, during operation of the blower, multiple rows of blades,

(1) the trailing edge of the forward blades and the leading edge of aft blades is separated by an axial distance, the axial distance between the trailing edge of the forward blades and the leading edge of the aft blades is equal to or less than the absolute value of approximately 0.12 times the chord of the aft blade of the multiple rows of blades for each pair of blade rows,

(2) the leading edge of each aft blade and the trailing edge of the forward blade nearest the upper surface of said aft blade is separated by circumferential distance, the circumferential distance between the leading edge of each aft blade and the trailing edge of the forward blade nearest the upper surface of said aft blade is equal to or less than 0.33 times the pitch of the aft blades for each pair of blade rows,

(3) each row of blades of said guide vane rows having a combination of chamber and blade solidity wherein, during operation of the blower, the direction of discharge from said impeller blades is turned by said guide vane rows back to the direction of the entry of said row into said impeller blades, the deflection of flow being greater than approximately 49°

, and

d. the pressure coefficient for each of said centrifugal blower stages is greater than approximately 1.1.

2. In a blower or pump as described in claim 1 in which

a. each of the blades in the forward row have a blade solidity equal to approximately 1.3±

0.6,

b. each of the blades in the aft row has a blade solidity equal to approximately 1.1±

0.6, and

c. the ratio of the guide vane exit fluid velocity to the guide vane inlet fluid velocity is equal to approximately 0.28 or more.

3. In a blower of a centrifugal turbomachine type as described in claim 1,

a. the absolute blade exit velocity of the impeller blades at the outlet is greater than the circumferential velocity and the inlet relative velocity, and

b. the flow vector of the circumferential component of the relative velocity of said impeller blades at the inlet is in a direction opposite to the direction of circumferential velocity and the flow vector of the circumferential component of the relative velocity of said impeller blades at the outlet is in the same direction as the circumferential impeller velocity.

4. In a blower of the centrifugal type as described in claim 1 in which

a. the aft row blades of said guide vane rows includes a plurality of part blades,

(1) each part blade having a chord equal to approximately one-half times the chord of the aft blade,

(2) each part blade having a trailing edge thereof located on the same line as the trailing edge of the aft blades of said guide vane rows,

(3) each part blade being disposed intermediate adjacent aft blades to form two flow channels between said adjacent aft blades, each flow channel having equal amounts of flow and approximately equal rates of flow deceleration therethrough, and

(4) each part blade having solidity equal to approximately 1.1±

0.6.

5. In a blower of the centrifugal turbomachine type as described in claim 1 in which

a. each of the blades in the forward row of said guide vane rows includes means for adjusting pressure and flow velocity through the impeller blades during the operation of the blower at a predetermined speed of operation,

(1) said means including means for mounting each of the forward blades for pivotal movement about a point located closely adjacent the trailing edge of each blade in said forward row, and

(2) said means including means for pivoting each forward blade about said point thereby changing the angle of attack of each blade of the forward row.